CN108349585A - Fluid propellant system and thrust and lifting force generator for aircraft - Google Patents

Abstract

The present invention relates to a kind of aircraft comprising main body and the gas generator for generating gas stream.It is connected to generator at least one front conduit and tail portion catheter fluid.First front injector and the second front injector are fluidly coupled at least one front conduit.At least one tail portion injector is fluidly coupled at least one tail portion conduit.Front injector respectively includes the export structure for the gas outflow from least one front conduit.At least one tail portion injector includes the export structure for the gas outflow from least one tail portion conduit.First primary foil element and the second primary foil element have respectively located immediately at the leading edge of the first front injector and the second front injector downstream.At least one secondary foil element has the leading edge located immediately at the export structure downstream of at least one tail portion injector.

Description

Fluid propellant system and thrust and lifting force generator for aircraft

Copyright statement

The disclosure is protected by the U.S. and international copyright method.2016 Jetoptera.All rights reserved.This patent A disclosed part for document includes material protected by copyright.Copyright owner do not oppose anyone to patent document or Patent disclosure makes a fax copy, because it is appeared in Patent and Trademark Office's patent document or record, but protects in other aspects Stay all copyrights.

Prioity claim

This application claims the U.S. Provisional Application No.62/213 for enjoying September in 2015 and submitting for 2nd, 465 priority, Complete disclosure is by reference to being incorporated herein, as fully expounding herein.

Background technology

It can hover, take off is commonly known as (VTOL) aircraft that takes off vertically and land with the aircraft of vertical landing.This point Class includes fixed wing aircraft and helicopter and the aircraft with tiltable power rotor.Certain VTOL aircrafts can also be other It is operated in pattern, for example, short takeoff and landing (STOL).VTOL is V/STOL (vertical and/or short takeoff and landing) Subset.

For illustrative purposes, the example of the current aircraft with VTOL abilities is F-35 Lightning.Guiding is vertical The conventional method of lift air-flow includes being used in connection with two groups of flat baffle blades using nozzle, and the nozzle can be along single direction Rotation, two groups of flat baffle blades, which are 90 degrees to each other, to be arranged and at external nozzles.Similarly, F-35 The combination of vectored thrust of the propulsion system of Lightning using the lift fan of vertical orientation and from turbogenerator carries For vertical lift.Lift fan is located at cockpit rear in the cabin with upper and lower biparting arc-shaped door.Engine passes through three axis Swivel nozzle exhaust is held, the three bearing rotaries nozzle can be by thrust from horizontal deflection to vertical front.Rolling control pipe Road is stretched out from each wing, and thrust is supplied by the air from engine blower.Pitch control is by lift wind Fan/motor power division influences.Sideway control is the weaving by engine swivel nozzle.Rolling control passes through differential Ground opens and closes the hole in the end of two rolling control pipelines to provide.Lift fan is sprayed with telescopic " D " shape Mouth to provide thrust deflection along the longitudinal direction.D-shaped nozzle has fixed blade at outlet opening.

What the design of aircraft or UAV was more generally useful integrated by its propulsion element and by these elements Body is constituted.Routinely, the propulsion device in aircraft can be turbojet, turbofan, helical turbine Paddle motor or turboaxle motor, the piston engine or electro-motor equipped with propeller.In small drone (UAV) Propulsion system (propeller) is routinely piston engine or provides the electronic of power via one or several axial propellers Motor.For the propeller of larger aircraft, either someone or nobody, be all traditionally jet engine or turbo-propeller Engine.Propeller is usually attached to the fuselage or ontology or wing, the pylon or pillar of aircraft via pylon or pillar Aircraft can be transferred force to and maintain load.The mixing jet (jet stream jet flow (efflux)) of the air and gas of appearance is The things of aircraft is promoted along the direction opposite with the flow direction of jet stream jet flow.

Routinely, the air-flow jet flow of large-size propeller is no in horizontal flight is used for lift purpose, and therefore a large amount of Kinetic energy be used for aircraft benefit, unless its as in existing certain applications today rotation (that is, Bell Boeing V-22 Osprey) other than.Certainly, the lift on most of existing aircrafts is generated by wing and empennage.In addition, even In Osprey in the specific VTOL applications (reaching horizontal flight by transition for example, taking off) of those of discovery, by propeller Lift caused by itself is minimum during horizontal flight, and the major part in the lift still comes from wing.

Current techniques state for generating lift aboard is to generate high-speed flow above wing and airfoil element, The wing and airfoil element are typically aerofoil profile.Aerofoil profile is characterized in that mainly directed in the axial direction after the leading edge of aerofoil profile extends to The chord line of edge.Based on the principle for being formed by the angle of attack between incident air flow and chord line, and being generated according to profile lift, The air of lower pressure flow through suction (on) side, and on the contrary, by Bernoulli's theorem be higher than downside (on the pressure side) rate (speed) it moves.The air speed of aircraft is lower, and lift is lower, and needs higher aerofoil surface product or higher incident angle, Including when including taking off.

Large-scale UAV is unexceptional to this rule.Lift is that have the angle of attack appropriate, wing chord, the span and mean camber line by design Air-foil generate.Wing flap, slit and many other devices are for being accumulated via increase lift coefficient and aerofoil surface Make lift maximumlly other conventional tools, but it will generate lift corresponding with the air speed of aircraft.(area increased (S) and lift coefficient (C_L) allow according to formula L=1/2 ρ V²SC_LSimilar amount of lift is generated under relatively low aircraft airspeed (V0), But cost is higher resistance and weight.) these current technologies also perform poor, imitated under conditions of with upper side wind Rate declines to a great extent.

Although smaller UAV may use the thrust generated by propeller to promote aircraft, current technology is tight The control of electro-motor rate is depended on to lattice, and smaller UAV there can be or can not have such ability, that is, described Ability is rotation motor to generate thrust and lift or be transitioned into horizontal flight by tilting propeller.In addition, being pushed away using these Into element smaller UAV by poor efficiency related with battery, power density and large-size propeller, the battery, power are close Degree and large-size propeller can be efficient in hovering, but inefficient in horizontal flight, and due to the point of blade quickly moved It holds and generates in operation difficult and dangerous.Most of current four-axle aircrafts and other Electric aircrafts can only have very Short flight time, and efficiently cannot promote or carry larger payload, such as flight whenever electronic horse It can be considerably beyond the 70% of the weight of aircraft up to system and the weight of battery.Using jet fuel or it is typically used for transporting In the similar aircraft of any other hydrocarbon fuel will carry the available fuel of at least one order of magnitude more.This can pass through It the energy density (high at least one order of magnitude) of considerably higher hydrocarbon fuel and lower is based on compared with battery system The ratio between the weight of the system of hydrocarbon fuel and total aircraft weight are explained.

Therefore, in aircraft, for UAV and some manned vehicles, the efficiency improved, improved energy are needed Power and other technological progresses.

Description of the drawings

Figure 1A to Fig. 1 C show between conventional electronic four-axle aircraft and one embodiment of the present of invention structure, power and Certain differences in control.

Fig. 2A is the vertical view of conventional airfoil and aircaft configuration；Fig. 2 B are the front views of conventional airfoil and aircaft configuration.

Fig. 3 is the sectional view of one embodiment of the present of invention, only shows the first half of injector and shows in inside The distribution of speed (velocity) and temperature in flowing.

Fig. 4 is the embodiment of the present invention, shows to be placed on propeller/injector in front of aerofoil profile.

Fig. 5 is an alternative embodiment of the invention, wherein a part of the propeller/injector as another air-foil It is placed on the front of control surface.

Fig. 6 A to Fig. 6 C show of the invention shown in Fig. 5 from different visual angles.

Fig. 7 A are another embodiments of the present invention, using in its wake flow jet stream jet flow and aerofoil profile push forward Aircraft and lift is generated, to replace the engine on wing.

Fig. 7 B are front views of the invention shown in Fig. 7 A.

Fig. 7 C are an alternative embodiment of the invention characterized by tandem wing.

Fig. 8 A are the side views of another embodiment of the present invention, it is characterised in that tandem thrust/lift generating system, Its middle front part thrust augmentation injector generates thrust by canard and back pressure enhancing injector is generated in tail region and pushed away Power and lift.

Fig. 8 B are perspective views of the invention shown in Fig. 8 A.

Fig. 9 is perspective view of the invention shown in Fig. 8 A and 8B and it is characterized in that airplane tail group device and gas hair Raw device pedestal.

Figure 10 A to Figure 10 E show that the lift coefficient at the constant space velocity of aerofoil profile changes, as showing stalling angle The function of incidence angle.

Figure 11 A to Figure 11 B show that the stall margin under the different location of the present invention is improved.

Figure 12 A to figure 12 C be the present invention another embodiment, it is characterised in that in in the relevant position of wing The injector part of propeller.

Figure 13 A to Figure 13 C show the present invention how using thrust augmentation injector and the wake flow for being placed on injector In thin airfoil pull together to control the pitching, rolling and sideway of aircraft.

Figure 14 is one embodiment of the present of invention, is had to the flap wing elements of the diffuser wall of coanda injector, The coanda injector itself is divided into two halves.

Figure 15 A to Figure 15 C show the 3D features of one embodiment of the present of invention from different visual angles.

Figure 16 A show an alternative embodiment of the invention to improve the performance and nargin of stall.

Figure 16 B to Figure 16 D show of the invention shown in Figure 16 A from different visual angles.

Figure 17 A to Figure 17 C show another embodiment of the present invention.

Figure 18 A to Figure 18 C show the typical conventional arrangement for coanda formula injector.

Figure 18 D are one embodiment of the present of invention, show to have the round coanda of simple primary nozzle element to spray Emitter.

Figure 19 A to Figure 19 D show different embodiments of the invention characterized by the primary nozzle with preferable performance.

Figure 19 E show the flowing above the dalta wing barrier placed in the center of primary nozzle.

Figure 20 explains the thermodynamics of the embodiment of the present invention.

Figure 21 is another embodiment of the feature and the present invention for improving flow separation delay.

Figure 22 A to Figure 22 F show the different 3D features and embodiment of the present invention.

Figure 23 shows certain features according to an embodiment of the invention.

Figure 24 demonstrations are such as applied only to the coanda formula injector of the aircraft for VTOL.

Figure 25 is shown as the alternative arrangement of the injector of an alternative embodiment of the invention.

Figure 26 A show high bypass (high-bypass) turbofan.

Figure 26 B are shown as one embodiment of the present of invention, modification as gas generator turbofan and start Machine.

Figure 27 A are one embodiment of the present of invention characterized by aerial drainage (bleed) and conduit network.

Figure 27 B are another embodiments of aerial drainage and conduit network.

Figure 27 C are another embodiments of the aerial drainage and conduit network that show controller and sensor.

Figure 27 D are another embodiments of the aerial drainage and conduit network that show controller and the sensor of identification.

Figure 28 A to Figure 28 E are the possibility shapes of the propeller of the present invention.

Figure 29 is possible layout of the propulsion system when taking off or hovering in one embodiment of the invention.

Figure 30 A to Figure 30 B show the thermodynamic cycle of jet engine.

Figure 31 is one embodiment of the present of invention.

Specific implementation mode

The application is intended to description one or more embodiments of the invention.Will it should be understood that such as " necessary ", " will " and class It will should be interpreted that like the use of word absolute terms and specific quantity and be applicable to embodiment as one or more, still It is not necessarily applicable to all such embodiments.As such, the embodiment of the present invention can be omitted or be included in this absolute terms The modification of one or more features or function described in context.In addition, the title in the application is merely used for reference purposes, and And meaning or the explanation of the present invention should not be influenced in any way.

The present invention disclosed herein independently and together to work allows UAV without using large-size propeller or fan In the case of execute the motor-driven of electronic UAV, and also make the independence, range and the ratio between payload and total weight of aircraft simultaneously It maximizes.The electronic UAV of such as four-axle aircraft can hover, takes off vertically and land, like this by simply control and its The rotating speed of the propeller of attaching executes circuit etc..The present invention eliminates the needs to propeller or large-scale fan, and mainly The control logic of the rotating speed to replace propeller is controlled with the fluid of the thrust augmentation injector of rotation, the thrust of the rotation increases Strong injector is powered fluid from carry-on gas generator.When compared with electronic UAV, using jet engine On-electric UAV typically without operating or not efficiently operating under the low speed, and its mobility is restricted.Figure 1A is extremely Fig. 1 C are shown between the fluid four-axle aircraft of one of conventional electronic four-axle aircraft and the embodiment of the present invention in structure, power With certain differences in rotating speed.

Invention introduces several elements for the mobility for significantly increasing on-electric UAV.For example, the reality of the present invention It applies example and discloses a kind of novel propulsion device (propeller) that can be disposed aboard.Another embodiment describes as pushing away The novel 3D elements realized in injector into a part for device.Another embodiment, which discloses, (promotes thrust generator Device) and the series system combined of thin airfoil wing (lift elements), the thrust generator (propeller) and thin wing Both type wings (lift elements) can be disposed aboard.Another embodiment describes a kind of specific series system, The series system is made of injector nozzle and the thin airfoil being placed in the wake flow of nozzle, and using from nozzle Jet flow is sprayed for generating thrust and lift.Another embodiment discloses novel placement of the injector on wing to allow It flies for higher incidence angle.Another embodiment discloses the application of the thermodynamic cycle of propulsion system, has and improves The optional favorable characteristics of the total weight of efficiency and reduction propulsion system.Finally, another embodiment describes a kind of thrust generation System, together with the control combination of pitching, rolling and sideway by VTOL abilities with turbomachinery and to aircraft.At this Each of more embodiments of previous embodiment disclosed in application and the present invention will be solved further in the following paragraphs It releases.

Propulsion device and push system

Fig. 2A and Fig. 2 B describe the conventional airplane for the engine installed with wing, the engine production of the wing installation Raw thrust, the thrust generate the acceleration and rate of aircraft, this causes to generate lift on wing；The function of engine is production Raw thrust, and the jet stream jet flow from engine is not used in and further generates lift, but it can be lost in environment.Jet stream Jet flow have than aircraft fast speed, and as such, by wing generate lift be aircraft air speed function without It is the function of local engine jet stream jet velocity, is the target of current application.

One embodiment of the present of invention includes propeller, and the propeller is used to carry secretly and accelerate using fluidics Surrounding air, and by high pressure gas (being supplied to propeller from gas generator) and entrainment surrounding air mixture height Rapid fire stream jet flow is directly toward such aerofoil profile conveying in a manner of engineering design, that is, the aerofoil profile is with symmetrically or non-symmetrically Mode is just placed on the rear of propeller in the wake flow of propeller jet stream.

Fig. 3 only shows the sectional view of the first half of injector 200.Pumping chamber 211 is supplied to the gas hotter than surrounding air Body.The pressure that can be generated by the engine or motor compressor of combustion of fossil fuel for unrestricted example is dynamic Power gas stream 600 is connected to the inside of injector via conduit and primary nozzle 203.Each design of primary nozzle 203, it is primary Nozzle accelerates to motive fluid 600 by the rate needed for injector performance.Primary (power) fluid 600 exists as wall jet flow To occur at a high speed on Coanda surface 204, it is entrained with surrounding air 1, the surrounding air 1 may be at stationary state or from attached Injector is approached in the left side of figure with non-zero rate.The mixture of stream 600 and environment 1 pure earth's axis at the throat 225 of injector To movement.By the diffusion in diffuser 210, mixing and smoothing processing persistently carry out, so the in axial direction temperature of (700) The distribution of degree (750) and speed is no longer with as they are present in high level and low value at throat 225, but going out in injector Become to be more uniformly distributed at mouthful.As 600 and 1 mixture approaches pelvic outlet plane, temperature and VELOCITY DISTRIBUTION are almost uniform；Especially It, the temperature of mixture is low enough to be guided towards aerofoil profile, and the aerofoil profile is, for example, wing or control surface.

In fig. 4 it is shown that an alternative embodiment of the invention, wherein propeller/injector 200 are placed on aerofoil profile 100 Front and generate lift 400.Due to 300 higher of speed of the 200 outlet jet jet flow of propeller compared with aircraft airspeed 500, So the local flow on aerofoil profile 100 has the rate higher than the rate of aircraft.Propeller will with higher entrainment rate The relatively heat power stream provided by gas generator is tempestuously mixed with the colder surrounding air stream entered.Mixture is enough homogeneous , the temperature of the heat power stream 600 of injector is reduced to, mechanically or in structure aerofoil profile 100 or 150 is generated by no The mixture temperature distribution 750 of influence.The VELOCITY DISTRIBUTION for leaving the jet of propeller 200 makes it will be due to higher office Portion's rate and allow to generate more lift 400 by aerofoil profile 100.Additional control surface can be implemented in aerofoil profile 100, example Such as, elevator surface 150 depicted herein.Pass through the angle on surface as change 150, it is contemplated that jet stream jet flow 300 compared with The posture of high local velocity, aircraft can promptly change under smaller effort.

Fig. 5 shows that propeller/injector 200 can also be used as the part of another air-foil 101 and be placed on control The front of control surface 152.Propeller can be nonaxisymmetrical shape, and control surface can be just placed on described push away Into in the wake flow of device 200.Propeller with higher entrainment rate by the relatively heat power stream provided by gas generator with enter Colder surrounding air stream is vigorously mixed.Similarly, mixture is enough homogeneous, by the temperature of the heat power stream 600 of injector Degree is reduced to will be without mechanically or in structure being distributed the mixture temperature that control surface has an impact.In this embodiment, Sideway can be controlled by changing the orientation of control surface 152.The major function of propeller 200 is generation thrust, but it Generate lift or gesture stability.In this embodiment, sideway control is to surround axes of aircraft 10 along direction 151 to generate Rotation.

Fig. 6 A to Fig. 6 C show the diagram in Fig. 5 from different visual angles.

For example, due to the rectangle exhaust plane of propeller there is the emerging jet stream of rectangular patterns can also compare spiral Paddle and electro-motor are easier and carry out vector quantization in more direction.In another example, since the rectangle of propeller is arranged Gas plane and emerging jet stream with rectangular patterns are by towards being placed on short wing at a certain distance from the rear of propeller Leading edge guide to maximize promotion benefit.As described in the invention, propeller therefore can be along the side with jet stream jet flow Thrust necessary to advancing forward for aircraft is generated to almost opposite direction.In addition, with the high rate of the rate than aircraft The move and jet stream jet flow caused by the propeller or injector will be used to increase lift, and the lift is by being placed on Produced by flowing on the aerofoil profile at the propeller or injector rear.The speed of jet stream will always need speed more than aircraft Degree, and the difference between two speed will need to be minimum, to maximize propulsive efficiency.It can be seen that lower But the mass flow that thrust is provided under the rate higher than aircraft rate is higher, and propulsive efficiency is higher.For example, using by this field Propulsive efficiency equation known to technical staff：

PE=2V0/ (V+V0)

Wherein V is propeller outlet jet speed, and V0 is the air speed of aircraft, if propulsive jet speed is aircraft sky The 150% of speed, then the air speed of aircraft by be the propeller occurred effluxvelocity 50%, and propulsive efficiency will be 80%. After the exhaust section for the propeller for leaving aircraft, the exhaust stream of most conventional jet plane is lost in environment, and Do not benefit from remaining jet stream, but the jet stream from such as jet engine still carries energy in wake flow.Exhaust Flowing is typically round jet stream, is mixed with PARALLEL FLOW and finally with relatively low with higher rate (and therefore for energy) Rate is with Aircraft Training Vortices to mixing.Once exhaust stream action leaves aircraft engine for exhaust, then jet stream jet flow there is no Beneficial to aircraft, and the speed of exhaust jet stream is higher, and propulsive efficiency is lower, and energy dissipation is in the environment.

One embodiment of the present of invention utilizes the mixed flow occurred from propeller of the present invention, and the mixed flow will be with other sides Formula is lost in conventional airplane in environment, and the mixed flow straight line is directed to thin airfoil wing or directly placement will pass through It generates lift on other surfaces at the propeller rear or generates direction and change ability, for lift generation or aspect Change.Since the supply of compressed gas can be via the network for being included by airframe and wing in segmented fashion by into one Step system or use, thus jet entrainment and speed can be conditioned via main method or secondary method (dialed).Main method be finger pressure, flowing, temperature and/or segmentation (it is multiple segmentation be supplied to distributed across aircraft it is multiple Propeller) modulation.The concept of segmentation is related to easily spreading all over the use of multiple thruster elements of aircraft placement, that is, will be single It is a large size propeller function be divided into multiple smaller propellers, the multiple smaller propeller via conduit network Gas-pressurized is supplied.Secondary method can be related to changing position or geometric form of the propeller relative to the neutral position of the propeller Shape.For example, in horizontal flight, supplying gas pressure appropriate and flowing to propeller can cause the 125% of aircraft airspeed The jet stream jet flow at place.In the case where 125% jet stream jet flow axial velocity is more than aircraft airspeed, propulsive efficiency becomes 88%.Such as The speed that fruit occurs in the case where generating identical thrust level via the entrainment of surrounding air becomes under higher rate 110%, then propulsive efficiency be increased to 95%.

Thrust and lifting force generator

An alternative embodiment of the invention relates generally to the combination of the thrust and lift that are obtained via series system, institute It states series system to be made of thrust generating device, the thrust generating device is by the height with almost axial direction velocity component The non-circular jet of speed is directed on the thin airfoil in jet downstream.The high axial velocity in part of the jet Generate lift in wing more common than aircraft rate it is considerably higher it is horizontal under lift, such as~(effluxvelocity)².Jet flow is penetrated Stream is the mixture of high energy hot gas and the surrounding air of entrainment, and the high energy hot gas is exported from high pressure gas generator and passed through It is provided to thrust generator by conduit.The air of entrainment is by being supplied to the high pressure of the thrust generator in thrust generating device Gas transmits via momentum and is brought into kinetic energy bottom horizontal flow sheet.The mixture of generated air and gas is from thrust generator It is middle appearance and can be by the on the pressure side guiding towards thin airfoil leading edge and/or aerofoil profile to be generally directed to axial downstream direction.

In most of conventional airplane, jet can not possibly be guided at present in aerofoil profile or airfoil type (wingfoil) To utilize the energy of its loss.For turbojet, the high-temperature of jet stream jet flow actually eliminates it via the wing Type generates the purposes of lift.Typical jet-propelled delivery temperature is 1000 degrees Celsius, and when after-burning when increasing thrust for having Shi Genggao is such as true for most military aircrafts.When using turbofan, although in modern aircraft Upper to use higher bypass, apparent non axial direction residue element still has, this is because fan rotates, although blade Predominantly axially guide fan and core exhaust fluid.The presence of core hot gas at very high temperatures and appearance The residual rotation of mixture moves and the cylindrical nature of jet stream in downwash flow so that using being directly placed at turbine The aerofoil profile at Duct-Burning Turbofan rear is unrealistic.In addition, the hot-fluid of the jet engine from such as turbofan and The mixing length of cold flow is occurred with mile rather than with inch.On the other hand, larger turboprop is used at present Generation and the sizable downwash cylindrical streams of airscrew diameter size, in the journey of the rotational component speed of rear propeller Degree is higher, and so that large quantity of air is moved at lower speeds.Rotational component make it difficult to by downstream kinetic energy be used for except promote with Outer other purposes, and therefore a part for kinetic energy is lost and is not uses efficiently.Certain moved by large-size propeller A little air are also channeled into the core of engine.It is not yet developed at present in short, the jet stream jet flow from the system that currentlys propel has Dump energy and potentiality.

In this embodiment of the invention, it is directed to thin airfoil by the way that straight line will be flowed for lift to occur, which can be with It is used as lift to flow.For example, jet stream jet flow axial velocity ratio aircraft airspeed it is big 125% in the case of, pass through with the span The case where air speed cleaning of aircraft air, is compared, and the part for receiving the wing of jet stream jet flow can be that identical span generation is higher by 50% or more lift.Using the example, if jet stream jet speed increases to 150%, lift becomes than in aircraft airspeed Under original wing be higher by 45% or more, for example, if using the pressure exhaust from turbine, including density declines effect.

Alternatively, completed to take off manipulation and after rotating forward and changing to horizontal flight immediately in aircraft, such as light-duty machine The wing of aerofoil profile can directly be deployed in the injector pelvic outlet plane rear of propeller, hence for from the less of engine It helps to generate more lift for power.

Alternatively, using the embodiment of the present invention, wing need not be equally long in the span, and for identical curtain Line, the span can be reduced beyond 40% to generate identical lift.By the lift equation known to those skilled in the art In：

L=1/2 ρ V²SC_L

Wherein S is the surface area of wing, and ρ is density, and V is the speed of aircraft (wing), and C_LIt is lift coefficient.In machine The wing is relatively thin and has the string similar with original wing, camber angle and C_LIn the case of, if during horizontal flight it is in office when It waits jet stream and is directly oriented to wing, the span can be reduced to only 6 feet by the UAV with such as 10 feet of the span.If Mixing ratio (or entrainment ratio) is larger, then the adverse effect of temperature on density is much smaller, and therefore jet temperature is only slightly higher.

Fig. 7 A, which are described, to be made jet engine be placed on wing and independently generates a kind of alternative of thrust. In fig. 7, jet engine no longer generates the jet stream jet flow for pushing aircraft forward, and is used as gas generator and generates Dynamic air-flow for a series of injectors for being pushed ahead in embedded wing for being provided with power.In this embodiment, Gas generator (not shown) is embedded in the body of aircraft, and green portion indicates entrance, gas generator and leads to The conduit of red injector, the conduit be it is flat and it is similar with wing flap or aileron can activated, so as in addition to provide The posture of aircraft is also controlled other than required thrust.Fig. 7 A further show to be placed in series with first (main) wing another (secondary) wing, described first (main) wing just at the injector rear and accommodate thrust augmentation injector.Therefore, Secondary wing receives the speed more considerably higher than the air speed of aircraft, and secondary wing generates higher lift like this, such as described Lift is square directly proportional to air speed.In this embodiment of the invention, the kinetic current due to being generated by gas generator Body (also referred to as secondary working fluid) is mixed with the secondary fluid as surrounding air, and secondary wing will be seen that the higher temperature of appropriateness, The secondary fluid is that have the rate of the secondary fluid between 5 parts to 25 parts to carry secretly with every part of secondary working fluid by motive fluid 's.As such, according to following formula, the temperature seen by secondary wing is slightly above environment temperature, but is significantly lower than motive fluid, To allow the materials for support of secondary wing and maintain lift load：T_Mixing=(T_Power+ER*T_Environment)/(1+ER), wherein T_MixingBe from The final fluid mixture temperature for the jet stream jet flow that injector occurs, ER are the surrounding air numbers of every part of Powered Air entrainment Entrainment rate, T_PowerIt is the hotter temperature of motive fluid or secondary working fluid, and T_EnvironmentIt is the ambient air temperature approached.

Fig. 7 B show that the front view of aircraft shown in Fig. 7 A, arrow indicate to be lacked on wing by shorter tandem wing Generated additional lift in the case of weary engine.

Fig. 7 C show an alternative embodiment of the invention characterized by tandem wing.In this embodiment, as pushing away Thrust augmentation injector 701 into a part for device system is placed on main wing (front wing) 703 and is connected with via conduit And receive motive fluid from the gas generator being placed in fuselage.Injector generates thrust and is transferred mechanically to power Aircraft.Jet generates constant high velocity stream, by secondary wing (grey wing) 702 for generating additional lift.Two The significantly larger span wing that the group composition and division in a proportion of a shorter wing lacks injector thrust augmentor generates more lift, institute Injector thrust augmentor is stated dependent on being attached to the larger wing to generate the jet engine of thrust.

Fig. 8 A and Fig. 8 B show another embodiment of the present invention.As shown in Fig. 8 A and Fig. 8 B, tandem thrust/liter Power generating system is attached to aircraft 804, is pushed away including the front of leading edge and intake section for entering upstream air Power enhances injector 801 and just generates thrust at canard rear, each in such injector is positioned in aircraft Starboard and larboard on.When horizontal flight, canard is oriented with higher incidence angle and close to stall, and wherein thrust augmentation sprays The presence of emitter extends the stall margin of the canard 803.Thrust is mechanically transmitted to structure by thrust augmentation injector 801 804 and the downstream jet stream jet flow that is made of well-mixed primary and secondary air stream is generated, again in wing 802 Generate considerably higher lift.The system also replicates on the tail portion of aircraft in a similar way.Thrust augmentation injector 801 from Gas generator 800 receives compressor aerial drainage, and tail portion thrust augmentor injector receives the combustion gas for leaving gas generator 800 The pressurized hot gasses of turbogenerator.It respectively will be for the compressor aerial drainage air of 801 injectors and for tail portion injector The combination that thermal exhaust is used as secondary working fluid causes：(1) the pushing away in horizontal flight caused by injector entrained ambient air Power enhances；(2) it is placed on the additional lift generated on the surface at the injector rear, the surface is, for example, to have leading edge Wing 802.These elements for being placed on injector rear are typically thin-slab structure, and can be gone out by composite material structure, Including but not limited to ceramic matric composite (CMC).The arrangement provides greater flexibility in the transition for flying to hovering from Period is switched to horizontal flight and landing.

Fig. 9 provides the more details of tail portion (or heat) section of the diagram in Fig. 8 A and Fig. 8 B.With up-front thin-slab structure 904 are placed in the wake flow of one group of hot thrust augmentation injector 901, before one group of hot thrust augmentation injector 901 has Edge and primary (power) fluid is received as thermal exhaust from gas generator 800, the gas generator 800 is located at cockpit 805 nearby and by air are entrained in the import 902 of injector 901.The exhaust of gas generator 800 is linked to element 901 conduit is embedded in vertical fins structure 950.Injector 901 is by the ambient air entrainment of entrance in entrance area 902 In and will outlet 903 at entrainment high-speed air and power gas mixture sprayed mainly towards thin tail structure 904, This generates additional lift again.Both elements 901 in element 801 and Fig. 9 in Fig. 8 A and Fig. 8 B can surround them Main shaft rotate for VTOL and Hovering control.Additionally, each injector of injector group 901 can surround with it is another One injector is identical and/or the rotation of independent axis.

Figure 10 A to Figure 10 E show various flowings and lift to incidence angle, the incidence emphasized in midpoint and each example Angle is corresponding.Increase with the incidence angle of given aerofoil profile, lift increases, until the separation in the boundary layer in aerofoil profile is just in maximum Until stall (referring to Figure 10 D) being determined after lift point.

Figure 10 A are confirmed in Fig. 8 A and Fig. 8 B with the lift of canard structure 803 and incidence shown in zero degree (0 °) incidence angle Angle, orbicular spot indicate that lift and streamline indicate the flowing around canard type.Figure 10 B to Figure 10 D show with incidence angle or The angle of attack increases to the increased result of lift of the structure 803 for the stall point being shown in detail at Figure 10 D.It crosses such as Figure 10 D Shown in aerofoil profile position (relative to incidence angle), for example, at the position shown in Figure 10 E, with flowing become turbulent flow, It can detach and streamline is no longer smooth, lift promptly reduces.As incidence angle increases, lift approximately linearly increases, still At incidence angle shown in figure 10d, lift reaches maximum value, crosses the maximum value, and flowing detaches on the upside of aerofoil profile. In Figure 10 E, there are recycle the loss of lift generated with increased resistance, by opposite flowing and boundary layer occurs Separation.This causes lift to be remarkably decreased and leads to stall.

Figure 11 A and Figure 11 B show that the feature lift curve of Figure 10 A to 10E, the second curve show the extension of stall margin, It is confirmed the case where injector is positioned so that its delay separation and promotes to suck boundary layer with the higher angle of attack relative to wing Under improvement of the lift for crossing stall point to incidence angle.In Figure 11 B, due to the presence of injector, lift continue increase and Not with the relevant stall of incidence angle.Injector is crossed to the vertex placement of aerofoil profile to be allowed to adhere to or avoid separation coboundary again The flowing of the flowing of layer, the top interlayer will be due to the wing there is no the injector for sucking the boundary layer The higher incidence angle of type and detach in other ways.Injector introduces low pressure regional area in its inlet, forces in the wing wing The boundary layer sucking developed on the upside of type.It is placed by crossing the canard of Fig. 7 C, Fig. 8 A and Fig. 8 B or the vertex of aerofoil profile 803 Thrust augmentor injector, stall margin become much larger.These results indicate that the presence of injector extends stall margin and permits It is allowable in generating bigger by the way that the stalling angle of the aerofoil profile is crossed in angle of attack increase there is no injector Lift.In addition, Figure 11 A and Figure 11 B show that injector is placed relative to the possibility of wing chord so that flowing is around aerofoil profile again streamline Change.

Figure 12 A to figure 12 C shows another embodiment of the present invention.Main wing and thrust augmentation ejector system generate Forward direction thrust and the adjustment of high-speed jet jet flow, work as and (are not shown with secondary aerofoil profile, but can be placed on the tail in injector downstream In stream or jet flow) connection when can be used for additional lift and occur.As shown in fig. 12, injector is by two (2) air knife shapes Half portion formed, they are together by using secondary working fluid or motive fluid and to spray secondary working fluid and secondary fluid at a high speed Final mixture comes the entrainment of generation environment air, momentum transmission and acceleration.Two half-unit 1201 and 1202 can be independently Rotation and translation relative to wing to position itself so that they are based on aspect and task (or point in task), primary Fluid situation (flow, pressure and temperature) optimizes enhancing at any time.This allows to be formed by throat one by two half-unit There is particular value in a example, but there is greater or lesser value in another example.For example, when taking off, two half-unit The two can be directed toward down so that aircraft can take off vertically.Two half-unit can move in position independently of one another in most So that thrust is maximized under big primary fluid flow and maximum entrainment rate, is conducive to make thrust maximized, certain to generate Area entry and the ratio between throat.However, when horizontal flight, two injector half portions can be horizontal and and machine instead Wing streaming together, the smaller throat region for the smaller pressure of secondary working fluid, temperature and flow make thrust augmentation most again Bigization.Throat region, exit region, entrance area and their ratio can also be adjusted according to the maximization of thrust algorithm Section.Both half portion 1201 and 1202 separately includes pumping chamber 1211 and 1212, be connected to conduit and sent out from such as gas The compressor aerial drainage port of raw device receives the secondary working fluid.Two half-unit forms variable inlet region 1201a and can be changed together Exit region 1201b and the diffusion shape formed respectively by wall 1213 and 1214, so that most preferably diverging flow is described to make Thrust maximizes.Secondary working fluid is divided via multiple nozzles 1203 and 1204 specially designed in a manner of continuous or pulsation respectively It is not introduced into throat region from pumping chamber 1211 and 1212.

Figure 12 C further describe the arrangement of the injector of the horizontal flight for aircraft.Figure 12 C are shown when in the disclosure When all elements of description are used for peak efficiency, flat jet can be inserted into the thickness of air-foil.Figure 12 C show institute The profile of injector the inner surface and the outer surface is stated, and Figure 12 B show the disclosed flat Ke's grace integrated with wing Up to the 3D models of the lower half 1201 of injector and the first half 1202.The two half-unit that can be independently actuated formed together into Mouth 1201a and outlet 1201b；They allow secondary working fluids by 1203 high speed of primary nozzle be introduced into Coanda surface 1204 it On.

Figure 13 A to Figure 13 C show the present invention how using thrust augmentation injector and the wake flow for being placed on injector In thin airfoil pull together to control the pitching, rolling and sideway of aircraft.About pitching, cold injector and thermal sprayer can surround Their main shaft is independently rotated to promote aircraft pitching forward or backward.Pitch control is pushed away by front/tail portion injector The modulation that power divided and/or be supplied to the dynamafluidal flowing of injector influences.About rolling, injector can independently turn It moves to promote aircraft rolling.About sideway, can use after surrounding the additional rotation of vertical axis and being located in jet stream jet flow The combination of thin airfoil in wake flow causes the change of aspect.The embodiment of the present invention is using rotatable, biography Make it possible that these are manipulated in the case of the special joint for passing to the injector with permission secondary working fluid of defeated load.

Coanda device

In yet another embodiment of the present invention, the propeller and/or thrust generator of series system have entrainment big Amount air and the ability for being accelerated to jet stream jet velocity.This is realized by using coanda device.These flowings Intensifier is generally described by different publications, and the different publication will beg in further detail below By.For example, papers " Theoretical Remarks on Thrust Augmentation " of the von Karman at him (Reissner Anniversary Volume, Contributions to Applied Mechanics, page 1949,461- Page 468) in be described in detail why coanda device causes considerably higher thrust augmentation via multiple jet streams.It is similar Ground, United States Patent (USP) No.3,795,367 (Mocarski) disclose a kind of air folder under the high enhancing ratio more than 1.8 The device of band, and a kind of linear coanda device is applied to jet engine by United States Patent (USP) No.4,448,354 (Reznick) VTOL abilities.In these above-mentioned publications and not referred in this in other bibliography, the application of coanda device is It is only limitted to VTOL and only VTOL is described, and be not applied to horizontal flight.One main introduction is to be used for horizontal flight Scalability and application it is not actual, for the axial symmetry device of coanda formula, size can induce larger The resistance of the aircraft of type increases.However, the application for small UAV can be more suitable for the integrated of higher degree.The reality of the present invention Injector and fuselage and engine or propulsion system can be integrated by applying example, this is because aircraft need not be taken into consideration Larger seating capacity.As disclosed integrate is unpractiaca in large scale business flight at present or in business in these embodiments On be unreasonable.

The embodiment of the present invention improves coanda device and applies the device using new technology, so as to preferably Entrainment and delay or avoid its in the device positive (aggressive) turning in detach.Although the compactedness pair of these devices In aviation and the deployment in other fields be vital in it, but in order to enhance air entrainment, intake section needs be compared with Big.Reznick thinks that circular element is more highly efficient than linear element.Mocarski show entrainment for thrust augmentation be to It closes important.Diffuser component needs long enough to ensure that the separation in boundary layer does not occur for portion in the device, and is blended in dress It completes in the exit set.Routinely, these diffusers are longer and have very gentle slope, so as to by boundary separation wind Danger minimizes.

The present invention shows to improve the entrainment in coanda device by such novel elements, that is, the novel elements Separation dependent on 3D geometry and fluid flowing effect and in coanda device avoids the utilization of technology.The present invention's is preferred Embodiment has the entrainment ratio between 3 to 15, preferably higher entrainment ratio.In another embodiment of the present invention, The device will be received from such as gas generator, piston engine (being used for pulsed operation) or the pressurized source of compressor or booster Power gas.Another feature of the invention is following ability, that is, is changed with changing geometry with extensional surface by withdrawing Become the shape of the diffuser wall of the flat jet for propulsion so that obtain maximum performance in all points of aircraft task. In addition, when jet stream jet flow is guided downwards using the diffuser wall disposed completely, it is no longer necessary to which entire injector is rotated 90 Spend the needs for VTOL and hovering.

Flap wing elements are introduced into the diffuser wall of coanda injector, Ke's grace by an alternative embodiment of the invention Diffuser wall itself up to injector is divided into 2 half portions, be shown in FIG. 14 as respectively similar with the air knife first half 1401 and 201 injector of lower half.Element 115 and 215 is actuator or connecting rod so that the surface can move to respectively in 110a and The desired diffuser positions at the places both 210a.

Another embodiment of the present invention discloses classification 3D entrance geometries and/or primary independent or work together Fluid slot 3D features avoid how pattern is significantly improved the property of propeller together with introducing flow separation on propeller Energy.For example, as shown in Figure 15 A to Figure 15 C, 2D entrances are replaced by 3D entrances.Figure 15 A are further shown separately to 15C to be changed There is entrance, larynx into multiple 3D elements of the disclosed injector of its performance on baseline and in same level The 2D injectors in portion and diffuser.

Entrance can also match the boundary layer profile forms at the vertex rear for the main air-foil for being formed in aircraft (as schemed Shown in 16A), therefore help to suck boundary layer and the whole stall of delay (improving across all nargin), in fig. 25 into one Step shows the position relative to aerofoil profile.Figure 11 A and Figure 11 B show to enter relative to described in the so placement of aerofoil profile and its boundary layer type face The benefit of mouth.

Figure 16 A show flat jet to wing structure to improve a reality of its higher incidence angle performance and stall margin Apply example.Injector feeds secondary working fluid from such as gas generator, and injector is positioned such that injector makes described Flowing streaming on aerofoil profile is to postpone stall.

Figure 16 B to Figure 16 D show that the different angle illustrated shown in Figure 16 A and injector are determined on wing Position, the pumping chamber that secondary working fluid is supplied to injector and their details with the relative position of aerofoil profile each other.

The injector described in fig. 14 has flat geometry and includes upper and bottom section, both It is generally perpendicularly introduced into motive fluid as the jet stream jet direction of wall jet stream and flowing or streamline in multiple slits, element 1401 and 201 can rotate independently about axis 102 and 202.Referred to as the curved wall of coanda wall 104 and 204 allows primary Jet stream follows curvature and in the process with more than 3：1 ratio carries secondary air secretly, the secondary air typically from Flowing above the aerofoil profile in the upper surface boundary layer of such as wing.Primary nozzle 103 and 203 have it is variously-shaped, it is described various Shape carries various 3D effects so that entrainment ratio maximizes, for example, triangle in Figure 22 B it is mini-wing 212 or primary nozzle 103 and 203 can be the fluidic oscillator fed by the pumping chamber, and motive fluid is supplied to generate in Ke in the pumping chamber Pulsed operation of the grace up to the powered fluid injection on wall.Fluid-mixing reaches at throat region (minimum area of injector) Purely axial direction.In addition to this, present invention introduces segmentation, movable diffuser section, for example, wing flap, as long as it is by making Capability vector and/or the maximization of the injector and play an important roll in the performance of the injector.

For example, when taking off, the wing that the entrance of the injector is fixed and is still located in Figure 17 A for being directing forwardly The top of type 1700.Figure 17 A show by upper (1401) half injectors and under this injector that is formed of (201) injector and nobody The deployment that the main wing to drive an airplane is pulled together.Two and half injectors can surround axis 102 and 202 respectively and rotate, and It can be translated according to mission requirements.Figure 17 B and Figure 17 C are shown below situation, that is, only upper half injector 201 initiatively with primary Fluid is used together, and 1401 are replaced by simple wing flap.As previously mentioned, 201 can surround axis 202 rotate and relative to Axial position translates.Half injector receives secondary working fluid from gas generator (for example, gas-turbine engine) under stress, and And secondary working fluid is allowed to pass through primary nozzle, the primary nozzle that fluidic oscillator may be used (that is, to be for example up to and include Certain frequency including 2000Hz pulses to generate the pulsation entrainment of secondary flowing).

In fig. 14, injector first half diffuser 210 is extended to form curved surface 210a and be directed downwardly toward mixed The primary and secondary of conjunction flows.Meanwhile lower diffuser 110 also extends into 110a, the adequate rate for keeping area to increase and Composite character is to obtain by the maximum thrust needed for aircraft.Certain parts in 110a and 210a can not be disposed, and 110 Hes 210 are independently controlled also according to scheduling appropriate.In addition, upper 201 element may or may not be axially moved to follow task Needs.In one embodiment, different amounts of secondary working fluid and/or the fluid conveyed at different conditions can be with continuous Or the mode of pulsation is supplied to 201 or lower 1401 elements.110a and 210a diffuser faces can include delay or avoid The pit of boundary layer separation and other elements.In addition, if fully extended 110a is utilized and potentially in specific location It is staggered and can be pulsed according to the operation mode of fluidic oscillator to supply pulsed operation pattern to injector, then it is secondary Nozzle can also be opened.

When receiving fluid from compressor aerial drainage portion, the temperature of Powered Air is relatively low.Hot junction portion from gas generator Exhaust (exhaust from turbine) for example for the pressure discharged in 30psi compressor airs and 5：Under 1 entrainment ratio For the power gas temperature of 1500F and the environment temperature of 100F, the temperature of mixture becomes 335 °F (180 DEG C), to this sky Air tightness is 1.6E-3slugs/ft3 or 0.84kg/m3, is declined about~30% from environment.As such, being promoted mainly when aerofoil profile is deployed in When into device rear, even if in view of density reduces effect, the entire span can also reduce~10%.For 10：1 entrainment ratio (it is better than 5：1 design) for, for the jet stream of 125% appearance of similar condition and aircraft airspeed, lift benefit higher, this It is because of the hybrid density bigger under the mixing temperature of~200F, and the liter generated on the span washed by jet stream now Power is~16%.In this example, wing can correspondingly reduce length.

Thrust generator

An alternative embodiment of the invention relates generally to a kind of novel 3D thrust generators, can be connect from pumping chamber Receive gas-pressurized, the entrainment sky under static or moving condition (including but not limited to the condition that those are more than 0.05 Mach) Gas accelerates air via momentum and energy transmission by high pressure gas and well-mixed fluid is directed to almost The non-circular jet of high speed of axial direction velocity component.Jet can be the environment temperature of high energy hot gas and entrainment The mixture of air is spent, the high energy hot gas, which is provided via the conduit exported from high pressure gas generator to thrust, to be occurred Device.The air of entrainment can by the propulsion device being supplied in thrust generator high pressure gas via momentum transmit and by Bring kinetic energy bottom horizontal flow sheet into.The mixture of generated air and gas occur from thrust generator and be generally directed to The opposite axial downstream direction in the direction of aerial vehicle trajectory.Well-mixed stream provides almost unidirectional cooler gas with high speed Stream can be used for promoting via the aerofoil profile being placed in the wake flow of colder jet stream, hovering, lift occurs and gesture stability.This All do not see in any conventional jet fuel engine push type aircraft.The thrust generator can be only from fuselage It stands, improved by the front or rear portion of fuselage insertion aircraft and/or in embedded wing for stall margin.

Reznick has invented a kind of circular apparatus, and primary nozzle is dismantled from Coanda surface, and does not therefore generate wall and penetrate Stream.Although Reznick instructs additional secondary fluid to be accepted due to being displaced to Coanda surface, the circular apparatus Application be stringent circular in shape, and therefore aircraft cannot be scaled up in more practical application larger Flowing, and for example, as resistance becomes increasing, still integrated with wing.In addition, these slits have also been seen Being simple in size and geometry, and that any specific 3D features are not presented for mixing enhancing.Present invention introduces streamlines The propeller of type generates the jet flow of rectangular shape at pelvic outlet plane, additional so that energy to be used to generate in thin airfoil Lift, this violates the circular application of Reznick and makes improvements, the circular application of the Reznick cannot along except Longer aerofoil profile other than its own diameter is used effectively for generating lift in horizontal flight, and cannot be deployed in To suck the boundary layer of wing on wing, as one of the embodiment of the present invention.

Primary nozzle geometry

It is noted that in the patent being described, the present inventor will not increase primary jet stream to secondary flow using any The feature in dynamic region, and therefore there is the limitation of the invention.In addition, there is no primary nozzles in coanda device Staggeredly, other than the presence of the Throndson of central primary nozzle, the central primary nozzle is not placed on coanda dress It sets, and is located in the center of the entrance perimeter of coanda primary nozzle.Therefore, primary nozzle is generally positioned at identical axis Into plane rather than staggeredly or primary nozzle be dimensionally different with the adjacent nozzle of identical size and shape. If this is optionally advantageous for round coanda device, between the opposite side of coanda primary nozzle The non-circular coanda device along the maximum sized length of its inlet face with constant clearance, by the round coanda device The thrust of generation will be distributed equally in the case of ideal but during horizontal flight, if occurred using this device Thrust, the then secondary air entered will be unevenly received into the device, and therefore thrust generation will be to wing structure And its design brings challenges.This is primarily due to be previously mentioned in the prior art, it is envisioned that these devices are in aircraft flight Starting and final stage at used, rather than as flown to from land and including hovering and horizontal flight including Propeller occurs for the single thrust of entire task.In fact, the invention of Throndson is only applicable to take off vertically and land and hang Stop, major impetus facility grasps the horizontal flight function that thrust is provided via turbojet or turbofan.Therefore, exist In its invention, including the device of coanda injector closes in horizontal flight and forms the aerofoil profile of wing, that is, from taking off No operation or inactive during horizontal flight after transition.On the other hand, Reznick teaches a kind of circular apparatus, institute Stating circular apparatus has the primary nozzle for being used for thrust augmentation, but the circular apparatus is not embedded in by wing for water Flat flight, but both inlet and outlets of the device are utilized, for other than as the generation thrust of the present invention.

Figure 18 A to Figure 18 D show the routine arrangement for coanda formula injector.Figure 18 A are shown from the prior art Traditional coanda injector of circular shape.Figure 18 B show the flat coanda type spray from the prior art in embedded wing Emitter.The source of secondary working fluid is gas-turbine unit, and injector optionally advantageously mean that for taking off vertically and It is cut off in horizontal flight.Figure 18 B include the element disclosed in the variable as Throndson, including diameter, angle and length Degree.

Figure 18 C are Fig. 3 of Reznick, and show another circular embodiment, wherein using the nozzle of height mixing And wall of the secondary working fluid nozzle far from injector.Therefore, primary jet stream is no longer wall jet stream.Reznick only covers injector Circular geometry, obviously mean due to the limitation of scalability for take off auxiliary.

Figure 18 D show that pumping chamber 211 is supplied with one embodiment of the present of invention of round coanda nozzle member Secondary working fluid, the secondary working fluid are accelerated by primary nozzle 203 and are used as wall jet stream and be injected on surface 204.

Throndson uses the injector of non-circular form, but also uses rectangular slot.Rectangular slot is in such application In be useful, but the shearing jet stream of the secondary air for approaching entrainment for generate limited surface.In fact, by upper The rectangular slot for stating inventor's description generates the jet stream entrainment feature for the rectangular slot perimeter for being directed to intended size, 2L+2h=2 (L + h), wherein L is the length of each slit and h is the height of each slit.If using the larger perimeter of primary nozzle, packet Including the influence for including 3D features, then significantly larger amounts of secondary flowing is carried secretly.As shown in Figure 18 A to 18D, by primary nozzle In a zigzag or the vertex of waveform (sinusoidal) wall is axially staggered, greatly strengthens the entrainment of secondary air, such as in the disclosure Introduction.Efficiency and the entrainment spy of injector are further enhanced via the pulsed operation of embedded fluidic oscillator by primary nozzle Sign.

Figure 19 A to 19D show the variation of certain propositions in primary nozzle for better performance.Figure 19 A are shown Along the zigzag configuration of the primary nozzle of the circumference of the entrance area of injector, and compared with simple slit perimeter, exposure One times is increased in the primary jet stream perimeter of secondary flowing, therefore via the middle development between the zigzag wall of primary nozzle Turbulent shear layer increase entrainment.Figure 19 B show have increased coarse perimeter to generate the rectangular slot of additional turbulent flow, And therefore compared with the original smooth wall of rectangular slot, entrainment is increased 1.5 times to 4 times.Figure 19 B are schematically shown just Grade jet surface explains the 3D structures of spine in the axial direction to secondary or the aeriferous area of folder increase.Though Between so usually secondary air is mainly entrained in two adjacent slots in rectangular slot arrangement and in outer radius slit side On, but entrainment is greatly strengthened via surface and 3D effects now.Figure 19 C respectively illustrate primary jet stream and secondary Jetstream, The turbulent flow generated by 3D features considerably improves the primary flowing in relatively short distance and is transmitted to the mixing of secondary flowing and momentum.Figure 19C shows that the interaction and flowing that are generated by the adjacent rough walls slit, wherein red arrow indicate secondary working fluid, and The secondary fluid of blue arrow instruction entrainment.Shear layer is formed along wall, and increased perimeter is for the primary of identical input Cause the considerably higher entrainment of secondary flow for flox condition.The pulsed operation of primary nozzle further enhances entrainment Than.

Another feature of the invention embodiment is that advantageous feature is introduced in primary nozzle (referring to Figure 19 E and figure 19E).It is well known that the flowing on dalta wing generates the vortex opposite with the direction towards dalta wing center.It is sprayed in primary Micro-features are placed in some or all in mouth to generate this vortex occurred from primary nozzle.In this case, The amount of notable higher secondary air is advantageously entrained in injector by vortex, enhances its mixing and with continuous or pulsation Mode transmit by from primary nozzle come out secondary working fluid carry momentum.

Figure 19 E explain the flowing on the dalta wing barrier in the center for being placed on primary nozzle, that it changes The pattern of flowing so that it significantly increases the entrainment ratio of normal primary nozzle slit, without changing pressure in flow And temperature.In particular, primary vortex core is towards opposite on the direction at the slit or the center of delta wing, from the area between slit Carry significant secondary fluid secretly in domain.

Figure 20 describes presently disclosed thermodynamic cycle, and working fluid and entrained fluids are developed to obtain higher thermal mechanics Efficiency.Figure 20 confirms that in promoting thermodynamic cycle figure, the entrainment of air will determine point D under lower temperature value and entropy Movement to the left, the point D indicate the admixture between primary gas and secondary air.This is for higher propulsive efficiency device It is advantageous, wherein large quantity of air is entrained and accelerates to lower outlet jet speed, is kept due to better quality flow Higher forces are horizontal, this is the key element for realizing higher propulsive efficiency.In fig. 19 a, by with 2x in the same plane The equilateral triangle of long perimeter shows the perimeter for increasing 2 times instead of each length of normal rectangular slot perimeter.It can pass through All vertex of slot wall are staggeredly further increased into perimeter in each plane (referring to Figure 19 B).This primary nozzle The result is that by uniformly being mixed in the shear layer in formation by as the amount increase of the fluid of the entrainment of a secondary fluid at least 15%-50%.If secondary air primary condition is low speed, the performance of rectangle and non-rectangle perimeter shape will not very not Together, however, when injector travels forward and the auxiliary air speed approached is significantly greater for example in 0.0 Mach and 0.25 Mach Between when, then by the way that the most inner side of primary nozzle and outermost spine are placed on the axial plane of the rectangular slot before The spine contour shape at side and rear, primary nozzle can also be significantly improved.In other words, each primary nozzle becomes now At 3D structures, it will postpone or predict the entrainment of secondary air in an efficient way, to improve whole entrainment rate.In Ke's grace Up in injector, optionally advantageously, quickly and in relatively short distance occur secondary air entrainment and mixed with primary air with It is transmitted for momentum.This and other 3D elements, which are added to primary nozzle, helps to improve the performance of the injector.

It is characterized in primary nozzle flow path with relevant another of primary nozzle such as used in this embodiment Introduce fluidic oscillator.These fluidic oscillators provide the switching for being for example up to 2000Hz between two adjacent primary nozzles It is flowed with alternating spray wall, and entrainment rate is improved via dynamafluidal pulsed operation.

Another implemented in the present invention is characterized in by the way that nozzle to be placed on to each position along Coanda surface Place and therefore via at multiple axial positions near wall in a manner of wall jet stream and increase secondary fluid entrainment and Primary flowing is introduced in mixed pattern to make nozzle and its feature interlock.For example, Figure 21 shows such embodiment, wherein when V-arrangement vortex generates feature and is staggered when compared with normal rectangular slot, and in the balance for injecting secondary working fluid quality stream later At least the 25% of total secondary working fluid is injected before.This injection before rectangular slot causes higher entrainment rate, described Higher entrainment rate is enough to significantly improve the performance of injector.In addition, in figure 21, nozzle 205 is before primary nozzle 203 Inject secondary working fluid.Nozzle 205 has a feature that the more favorably entrainment of secondary flowing is introduced via shear layer, and when with These nozzles 205 interlock in axial and circumferential the two when primary nozzle 203 is compared.Primary nozzle 203 has dalta wing feature, The dalta wing feature is provided with support leg, the support leg be connected to primary slot configurations its midpoint inside simultaneously And there is triangle wing structure, the triangle wing structure head on Primary fluid flow and be vortexed along direction opposite 2 with to generate and It is mixed that having carried secretly for the secondary working fluid caused by nozzle 205 and secondary fluid is consumingly carried secretly from the both sides of primary nozzle 203 Close object.The vortex and V structure of primary nozzle cause 10% to 100% entrainment to improve compared with rectangle, noninterlace slit And the overall improvement that the momentum of secondary flowing transmits is flow to from primary.

In addition, Figure 21 shows the better simply construction using the triangle winglet for adjusting (paced) in smooth wall slit, with Form the flowing of specific dalta wing and shear layer, the specific dalta wing flowing and shear layer and smooth wall rectangle primary slit Compared to entrainment ratio is advantageously increased 2 times or more.All these elements can be combined to obtain best entrainment ratio.This Invention is modified to the surface of flow separation delay via element 221.It is described by the way that pit is arranged on Coanda surface 204 Coanda surface 204 has the turning of relative active, and the primary flow direction for radially being originated from primary nozzle 203 is most short The axial direction opposite with thrust direction is changed to towards throat 225 on.It is rapid with triangle shown in Figure 19 D and Figure 19 E Stream device is pulled together, these pits prevent flow separation and significantly enhance the performance of injector.

Figure 23 shows certain features according to an embodiment of the invention.Specifically, Figure 23 will be used by Throndson Similar primary slot height is compared with the ratio used by Throndson to confirm the improvement of the embodiment of the present invention.Changing Into segregation lag pit be placed on Coanda surface in the case of, the radius of the turning of the embodiment and slot height it Than being less than 5:1.In fig 23, for similar slot height, radius R' is smaller than the R radiuses of the patent from Throndson by about 2 Again to 3 times.It can be seen that due to using log law model with more accretion in tandem with the pit on bending Coanda surface is used Polar region is from the purely radial flowing turning in the exit of primary slit to the pure axial flowing at throat, so can have Less than 5：1 ratio.As a result, followed by the considerably more rapid turning without flow separation, thus the throat of device can than by Throat greatly at least 25% to 100% specified Throndson.Compared with prior art, the half-angle of diffuser can also obviously more Accretion pole, to allow to implement considerably shorter diffuser and flow the faster momentum between secondary flowing in primary to pass It passs.As such, Figure 23 highlights the difference between the present invention and the prior art, especially in such as turbulator, primary nozzle, pit In the case of the prior art being improved with the element of the more enthusiasm of moveable wall.

Coanda injector

In general, the design of the coanda injector applied to aircraft has been described in many publications.For example, United States Patent (USP) No.3,664,611 (Harris) teaches the coanda formula in a kind of embedded wing for the purpose that takes off vertically and land and sprays Emitter.The device is inactive during cruise, referring to Figure 24.During Harris is not mentioned using jet flow for being arranged in tandem Generate more lift.In addition, the device is not applied to use under the conditions of flat fly by Harris.On the contrary, with conventional practice one It causes, which collapses under the conditions of horizontal flight in aerofoil profile wing.

On the other hand, Mocarski is instructed, in coanda injector, high energy secondary working fluid (also referred to as motive fluid) Principle as wall jet injection, and this device is to determine the low-pressure area of entrained ambient air, is followed by towards throat Region of convergence is mixed, followed by diffuser so that mixture is to expand back at a high speed environmental pressure.United States Patent (USP) No.3,819,134 (Throndson) concept described in Mocarski is changed and is improved.

Throndson is by the way that primary flowing to be added in the center of coanda formula injector further to carry secondary flow secretly The performance of body and enhancing nozzle describes the enhancing of the technology, wherein primary center nozzle using total secondary working fluid 30% to 70% and in coanda formula parameters Nozzle using balance.Throndson claims that this combination greatly strengthens thrust increasing By force, without explaining secondary working fluid nozzle geometry structure, the secondary working fluid nozzle geometry structure looks like simple narrow Slot or aperture.In addition, slit look like it is continuous or discontinuous, without specific feature.Throndson, which is not mentioned, to be made With jet for downstream generating lift, and in fact, it only by the device for taking off and transition and landing, and Non- Cruise Conditions, are very similar to Harris.

The present invention via coanda device under all flying conditions by being rotated to produce thrust and by will be thin Aerofoil profile is placed in jet stream jet flow and therefore generates more lift to be further improved coanda injector.This turbofan hair Motivation generally use surmount Harris and Throndson at least there are two advantage：

First, using the injector in the downstream of wing so that injector sucks its harmful boundary under Cruise Conditions Layer, improves the aerodynamic performance of wing and allows have higher incidence angle, to increase its overall performance.The present invention is also Injector is allowed to be operated from all stages taken off through the flight of hovering, transition, cruise and landing.One embodiment is also Allow to use half injector (by 1/ of the flat jet as described in Throndson or Harris in tandem with the wing flap of wing 2) asymmetrical coanda injector is formed, the asymmetrical coanda injector only carries secretly in the outer edge in boundary layer The boundary layer and diffuser is formed with the wing flap of the wing, including by making the wing flap and air-blade type Ke Grace makes the propeller vector quantization to be used for take-off and landing up to the injector coordinated movement of various economic factors.

Secondly, by horizontal flight the downstream of (but also for other flying conditions) on bottom line (spraying In the flushing of emitter) use thin airfoil, for generating additional lift in higher rate stream, with disclosed in aforementioned patent those It compares, this allows aerofoil profile and propeller to connect to become more compact and efficient while generating sizable lift.At this In the embodiment of invention, the shape and type of propeller jet, which face, realizes that its novel efficiency and functionality are to pass Important.The thin airfoil be placed on the pelvic outlet plane from the injector/propeller it is convenient with a distance from, also to spray Before the energy dissipation to environment for flowing jet stream, lift is made to maximize.Because the energy of any jet-propulsion plant is usually only flying It dissipates in the subsequent very long range of machine, so this is convenient and practical.

Also more important understanding is, concatenated two elements are required in a manner of efficient and optimization work together Make, including with to the advantageous certain angles of the concept and rate motion.Thrust component is mechanically transmitted to by thruster/propeller The fuselage of aircraft or its main wing, and in the thin airfoil Mechanical Contact fuselage rather than propeller in propeller downstream, but receive Its jet is grasped to make the lift of aircraft maximize and allow the movement via certain surfaces on the thin airfoil It is vertical.

Another feature of the invention is provided for promoting hang using identical nozzle and landing and cruise The ability of purpose.The lift system disclosed in United States Patent (USP) No.8,910,464 (Ambrose) indicates VTOL jet fighters Common trunk.It has office due to portable additional weight, that is, lift fan and its ancillary equipment in cruise mode It is sex-limited.Under current VTOL technologies, cold nozzle (front nozzle) and lift fan are closed during horizontal flight, this leaves main row Gas jets push ahead aircraft to provide reaction force under the conditions of the forward travel such as cruised.The implementation of the present invention Example combines the propulsion system of coanda nozzle thrust generating device and aircraft, and permission is adopted at all stages of flight With injector, to make the weight of moving component minimize and eliminate moving component.Furthermore it is possible to only during horizontal flight Special mode carrys out minimum esd resistance using this injector and maximizes lift.

Mocarski is proposed for continuous or discontinuous secondary working fluid slit (it is predominantly round or linear) The same technique of coanda device.In all these patents, Coanda surface is that round or 2D smooth types face is simple to determine Boundary layer attachment, without can enhance entrainment, increase Coanda surface actively turn or postpone its separation it is specific Element.In the injector of coanda type, it is essential that surface turning allow wall jet flow boundary layer growth and with Secondary air is mixed without becoming to detach.Once the primary stream motion from primary nozzle becomes to detach, coanda injection Device will be unable to efficiently operate or can not operate at all.It is most important that surface curvature allows maximum boundary layer to give birth to Long and secondary fluid entrainment and mixed and do not detached at wall.

On the other hand, if curvature is too big, which becomes impractically long and diametrically impractically big, Which also limits secondary fluid entrainment and mixed amount and induce the device very grow diffusion part.Throndson is retouched It is between 1 to state slit and the ratio between the radius of coanda turning：5 to 1：Between 15, but it is less than 1：5 ratio is for flipper turn For should be ideal.Throndson is clearly illustrated, and compared with the axis of device, the turning of coanda curve is ideally Between 30 degree to 110 degree.If diffuser becomes too big, this is for the deployment techniques for parallel aircraft in-flight For be important limitation, as the length of diffuser will bring significant additional friction and weight to aircraft.If turning becomes More than 110 degree, then diffuser can become shorter, and enhance mixing in considerably shorter distance, it is ensured that in mixture from dress Uniformly mixing and energy and momentum are transmitted to secondary flowing before being left in setting.It is noted that the wall of diffuser is also flat And the not 3D elements for enhancing mixed process.One embodiment of the present of invention is especially drawn in the diffusion zone of injector Enter to cross the moving wall of throat so that be conducive to taking off vertically and landing for aircraft, it is not necessary that entire injector is horizontal around it Axial-movement, but by extending the diffuser face of segmentation in the manner described below.

Coanda surface

If the Coanda surface instructed by Reznick, Mocarski and Throndson should be circular curvature, Throndson provides even more accurate details, that is, ranging from the 1 of the ratio between slit height and radius：5 until 1：15.By ability The technical staff in domain is preferably log law model, is penetrated without separation wall this is because it provides most fast boundary layer growth Stream.However, one embodiment of the present of invention realizes clearly more positive turning by introducing pit on Coanda surface To be significantly improved the turning on surface, to keep flowing while so that mixture is mixed and is moved in throat and diffuser Attachment.Preferably positive turning, this is because it is allowed for quickly mixing and flowing being made in axial direction to turn passing through Throat and enter diffuser section in ability.In fact, the turning of the fluid quickly moved can keep the attachment in boundary layer, and Simultaneously boundary layer growth and mixed with center flow.

Pit in the present invention can be of different sizes, can be staggeredly or alignment, can be located at turning In more positive region, rather than in the region of the turning of fluid less aggressively.Pit can also be used in more positive On diffuser, wherein the half-angle of diffuser is not constant but variable, and the half-angle of the diffuser grows and then subtracts It is small to 0, as shown in the element 105 in Figure 14.

Figure 14 shows one of the improvement realized by the present invention, especially when compared with Throndson.Figure 14 will be by Similar primary slot height is compared with the ratio provided in Throndson used in Throndson, to prove the present invention Improvement.Specifically, Figure 14 shows the first half and the lower half of half injector, they formed together it is better, more flexible and High performance injector can be adapted for taking off vertically and hovering and for the horizontal flight under Cruise Conditions.Lower part Primary nozzle wall jet stream is more positively utilized for (1401) half injector walls so that flowing is more energetically turned around axis 102 arrives table On face 103 (coanda inlet surface).The curved wall that the maximum height point of the curve is axially positioned in from element 201 (leans on Closely with blue shown in axis) the similar extreme lower position about point of " G " distance at.Therefore, two and half injectors (or air knife injection Wall) 1401 and 201 it is staggeredly, that is, and their entrance is not axially positioned at identical position.Similarly, 1401 With 201 minimum range axial position interleaved distance ' G', their diffuser 110 and 210 can be respectively by actuator 115 and 215 change shape, wherein the flat surfaces for forming 110 and 210 segmentation become crooked cross section 110a and 210a, Respectively in the injector interior downstream or along the various directions guiding flowing by task instruction.Figure 14 is also shown and existing skill Variation in the ratio that art is compared.

In addition, in the case where being placed with improved segregation lag pit on Coanda surface, the half of turning of the invention The ratio between diameter and slot height are less than 5：1.As a result, followed by the considerably more rapid turning without flow separation, so the larynx of device It portion can be than the throat greatly at least 25% to 100% that is specified by Throndson.In addition, the half-angle by applying diffuser component Constant variation (that is, non-linear growth of the wall far from center line) and uses on pit shape surface in the diffuser, institute Stating the size of the half-angle of diffuser component can grow without making fluid more energetically detach so that the total length of device contracts It is short.

In addition, if both the first half of injector and lower half are individually worked relative to fluid supply and functionality But it can work together for mixture to be carried secretly to, mixed and is diffused into outlet plenum, then by flat diffuser Additional diffuser moving wall in upper and lower surface the two greatly improves performance.This then also allows to pull together with wing structure Greater compactness of device is implemented for the propulsion reason in horizontal flight or in taking off vertically, hover and landing in ground, without Rotate total.

In addition, the use of pit allows wall to change from initial point, until the whole outlet around the periphery of the injector Until, therefore allow well to integrate with wing structure.Different structures is used at the rounded ends of injector, wherein primary spray Pit or special characteristic on mouth can not need injector and satisfactorily execute.Figure 22 A show have as described in the invention The injector of notable 3D features.In addition, in the most positive region of turning on the lower wall of diffuser, pit (Figure 21 is used In element 221) will also allow downward bigger to turn until 90 degree or even bigger.This than the prior art more actively (for example, Throndson；Referring to Fernholz, H.H. " Z.Flugwiss.15,1967, Heft 4, pp136-142).Figure 14 shows have The cross section of the injector of notable 3D features, as described in the disclosure.Being largely segmented on diffuser is also shown in Figure 14 Wall can reboot injector jet and can make its performance from the variation in diffuser region and Mixed Zone It maximizes.The plane of inlet of injector is not located in plane (on-plane surface), and therefore can injector be placed on wing Superstructure so that the sucking in boundary layer improves air-foil performance, such as in fig. 14 it can be seen that, in first half injector and There is size G (gap) between the two entrances of lower half injector.Therefore, Coanda surface (103 in Figure 14；In Figure 22 A 204) time history direction is early in the adjacent place of airfoil surface and later not at same axial position but in an axial direction Primary flow body wall jet stream is received far from air-foil surface.

Figure 22 A to Figure 22 F show that the different embodiments of the present invention, wherein 3D features are used in entrance.Figure 22 F features With first half injector.Figure 22 B are shown as the element 212 that triangle turbulator is placed in primary nozzle and such as 222 Pit, the element 212 considerably enhances the entrainment of secondary flowing, and the pit enhancing adheres to and even prevents from scheming The most positive turning separation of the coanda curved wall 803 of 22A to Figure 22 F and Figure 14.

In Figure 22 A to Figure 22 F, element 212 is also introduced into primary nozzle to enhance entrainment, and they can root Being used or not being employed according to condition enhances performance on the opposite side of injector.Pit 221 is placed on profile 204 and expands It dissipates on device to ensure the transmission of the good momentum in the shortest distance and generate secondary working fluid and secondary fluid as homogeneously as possible Mixture muzzle velocity and Temperature Distribution and avoid flowing separation.These secondary working fluids can be let out from compressor The mixture of the forced air in stream portion or pressure exhaust from gas-turbine unit or both, and can discretely feed To first half injector 1401 and lower half injector 201, another freedom is added to maximizing thrust luminous efficiency Degree.

In Figure 22 A, the increase of 3D features is exposed to the perimeter of flowing and is allowed for higher entrainment ratio.In Figure 22 B In Figure 22 C, the turbulator specially designed, such as the dalta wing that is placed in the center of primary slit, promote to come freely for example The flowing for the secondary working fluid pumping chamber that gas generator is constantly supplied is accelerated in access and is forced through the triangle Turbulator 212.Element 212, which forces, to be flowed into such pattern, that is, the pattern greatly improves secondary via a series of mechanisms The entrainment of grade flowing, a series of mechanisms include shear layer, rotation and counter-rotational turbulent flow and the increased primary The wetted perimeter of nozzle 203.It is also provided for via in Neighboring primary nozzle in the fluidic oscillator that primary nozzle is embedded in Pulsed operation come the additional capabilities carried secretly.

Figure 25 shows the arrangement with the injector of 3D entrances, on the lower lips (22) of wherein injector are closer Airfoil wall side 20 and the vertex for crossing the aerofoil profile, upper lip (23) axis with the injector further away from airfoil surface 20 Interlock to ground and is located in before the upper lip (23).The position of antelabium is modeled to match by the air-flow near aerofoil profile Caused most probable boundary layer velocity distribution (21).Compared with the entrainment of the lip 23 ' in boundary layer, pass through prediction lip 22 It carries the stream near airfoil wall secretly, obtains in the preferable distribution of inlet and injector performance.In the implementation of the present invention In example, injector can move up and down (along the direction vertical with upper airfoil wall) to optimize performance.It is handled by preferably entrainment, It will be allowed for obtaining preferable airfoil performance in the preferable aspect of performance of the higher angle of attack and injector itself.By the disclosure with The 3D elements that the prior art distinguishes include the position of inlet lip portion 22 and 23, the relative position of curved wall 204, throat region 24 Positioning and diffuser wall 25 positioning.In one embodiment, the two half-unit of injector can relative to each other and the wing Type independently moves, the position for causing the performance relative to aircraft constantly to optimize.

Figure 17 A to Figure 17 C show that the flat jet being placed in aerofoil profile, the flat jet form wing and have There is the two half-unit (referring to Figure 17 A) that can independently move, and such embodiment is also shown, that is, in the embodiment The first half of middle injector is only similarly used with air knife, but forms the throat of the wing flap with the wing being placed in aerofoil profile And diffuser, match required performance (referring to Figure 17 B).In these embodiments, wing flap may include or can not include just Grade nozzle, and wing flap is independently moved with first half injector, and the first half injector is also been described as air knife.This germline The advantages of system, is that it is better simply；It allows to have on wing still through wing stall is avoided via sucking boundary layer Higher incident angle as explained in current disclosure, and may independently rotate wing flap and air knife for optimization Performance and navigability.

In particular, Figure 17 A show the embodiment of flat jet as described above, the element of such as pit is on the vertex of wing Rear is placed on wing and so that it mainly sucks the boundary layer above the upper surface of wing.On the other hand, scheme 17A to Figure 17 C shows that the use of air-blade type injector, the air-blade type injector force the air of the sucking above wing (as secondary fluid) accelerates and pushes ahead aircraft.In all these examples, injector can rotate.In addition, In another embodiment, the entrance of injector can also be rotated in a manner of limited, but their diffuser wall can extend, As being explained further in fig. 14, as indicated by flying condition 1401 and 201, angle, exhaust gas region of change etc. can Independently to be rotated around axis 102 and 202 respectively.

Fluid propellant system and cycle

Another embodiment of the present invention relates generally to a kind of propulsion cycle transmitted via fluid momentum and provide thrust And system.Propulsion system includes：1) gas generator, the gas generator provide flowing to for several pressure-airs or gas source 2) compression fluid is directed to 3) the enhancing thrust of installation aboard at each station by conduit network, the conduit network Generating device.Enhance thrust generating device by the high speed jet jet stream with predominantly axially direction velocity component along desired direction Guiding, to generate opposite thrust.Jet is the mixture of high energy hot gas, and the high energy hot gas is via from height The conduit of pressure gas generator position (for example, compressor aerial drainage portion, burning aerial drainage portion, turbine aerial drainage portion and/or exhaust nozzle) Thrust generating device is provided, and the mixture of the high energy hot gas by such engineering design at very big entrainment speed Rate carries surrounding air secretly.In thrust generating device, the air of entrainment is by the high pressure gas for being supplied to the thrust generating device Body transmits via momentum and is brought into kinetic energy bottom horizontal flow sheet；The mixture of generated air and gas is from thrust generating device Middle appearance, and it is generally directed to axial direction towards the main pressure side of the thin airfoil leading edge and aerofoil profile, it is preferably directed to make The maximized direction of lift in the downstream aerofoil profile.

Fig. 2-7 shows one embodiment of the present of invention, it is characterised in that the propulsion device in VTOL configurations.Injector 201 and 301 are downwardly oriented, and thrust makes aircraft move upwards.Injector rotates synchronously, and the flowing of secondary working fluid Matching is modulated into spray from the compressor aerial drainage portion for injector 201 and the front and rear that is vented to for injector 301 The needs of the thrust of emitter.

Most efficient Conventional propulsion systems for middle long-range aircraft engine are high bypass turbofans.It is conventional Turbofan use at least two axis, one is by the shared axis of fan and low-pressure turbine, the other is being core The axis that the heart shares, the core can be made of boost motor, high pressure compressor and high-pressure turbine.Turbofan compared with High efficiency is caused by higher by-pass ratio, relatively low fan pressure ratio with the higher propulsive efficiency of determination；And by being led compared with high total pressure ratio Show and is used for higher thermal efficiency.The specific fuel consumption of aircraft and the product of heat and propulsive efficiency are inversely proportional.The heat of turbofan Loss mainly due in component (for example, compressor, turbine) burning and thermodynamic losses and machinery less than 100% Efficiency.In general, the irreversibility of combustion process is the main component caused compared with low efficiency, and typical high pressure ratio is dynamic The thermal efficiency of power equipment is only 40%.Practicability and other aircrafts limitation (weight, resistance etc.) hinder use as known in the art In the implementation for the method for improving the thermal efficiency, the method is, for example, cooling during rolling, recuperation of heat and other methods.

On the other hand, when propeller to be just above the air speed of aircraft and as close possible to the relatively small axial of the air speed of aircraft When speed accelerates the maximum amount of air mass flow, propulsive efficiency is maximized.This promotes to need to have very big fan diameter With higher fan speed, the resistance and weight of aircraft are increased.Currently, if the size of the diameter of fan is more than 11 feet, most Efficient turbofan is very big.Although increased fan diameter improves propulsive efficiency, due to radome fairing Size and increase resistance, and usually execute compromise to obtain ideal system.The level of current propulsive efficiency is more than 85%, and be dedicated to distributing thruster on wing so that it is maximized.The popular idea of one of this field is pushing away for distribution Into the concept of element.Thruster can be dispensed on the wing and fuselage of aircraft.In most cases, thruster is located in Fan and the reception mechanical work or electrical power from central location of electrical or mechanical driving on wing.Due to involved The complexity of network, the weight of electro-motor and they high altitude localities operability, and with regard to mechanical transfer network, For efficiency, complexity and weight, these concepts are difficult to carry out.Dominant Design is still two engine designs.

One of current dominant design is the disadvantage is that turbofan is heavy and complicated.30% or more of its total weight is only Only it is fan system comprising fan attachment and its low-pressure turbine of driving.Large-scale rotative component means there is additional set Meter limitation, including tip speed limitation, to the constraint of low-pressure turbine weight and size and the inlet temperature of low-pressure turbine.Wind Fan leaf needs qualified in the sucking of dedicated fan blade and fan blade output test and obtains certification.In addition, fan case needs It accommodates the liberation of this fan blade and protects the integrality of aircraft.For compared with mini system, if efficiency will be kept, Then the challenge of the turbofan system of scaled complexity is more notable.For UAV and baby plane, due to The limitation of material, by-pass ratio (BPR) are horizontal significantly smaller.It is reduced with the diameter of fan, fan needs quickly to rotate to protect Its efficiency is held, and tip loss occurs at higher speeds, so as to cause lower efficiency.Small sized turbine fan is sent out For motivation, challenge is, scaled fan (and compressor) means that rotating speed must increased dramatically.The technology of this field Personnel understand that the diameter of fan is to the square root of the quality stream of fluid directly proportional to be scaled, and the tip speed of fan and diameter (for example, Pi* diameter * RPM) directly proportional with the product of rotating speed.Therefore, if the diameter of fan significantly reduces, turn on the contrary Speed needs to increase to keep identical tip speed (for the reason of the machinery and compressibility), and otherwise performance loss significantly increases Add.For example, if a diameter of 50 inches of fan is rotated with 2000RPM, for identical tip speed, 20 inches Fan needs are rotated with 5000RPM, and 10 inches of fan is rotated with 10000RPM, and so on.This also means that fan Pressure ratio (FPR) will correspondingly increase, relatively low within the scope of small diameter so as to cause the efficiency of fan.In addition, it may be difficult to real This heavily stressed fan part is now accommodated, and thicker fan case will be caused, increase weight and will cause relative to being The notable complication of the rotor dynamics of system and its bearing subsystem.This is why large-scale fan is clearly more higher than small-sized fans The reason of effect.The present situation of small sized turbine Duct-Burning Turbofan is more apparent than large scale system to be less susceptible to execute, the small sized turbine fan hair The BPR of motivation is 3 times to 4 times at least lower than the BPR of large-scale fan, and small sized turbine Duct-Burning Turbofan has higher FPR, leads Cause lower efficiency (higher fuel combustion), higher rotation speed (elevated pressures and maintenance) and the operability with challenge and heat Management.Turbo-propeller engine is faced with same challenge, although for very small system, the very small system With best propulsive efficiency.Their major defect be need the propeller of large-size to make a large amount of air movement, and And it is difficult to implement in the system with VTOL abilities.Modern turboprop uses low-pressure turbine to drive propeller And additional auxiliary system is used, for example, gear and bearing and its subsystem, pitch control system and other.

Another element of the modern aircraft propulsive jet of such as turbofan and turboprop is Overboard discharge for the compressor of cabin pressurisation, turbine cooling and operability for engine itself needs a certain amount of Aerial drainage air.The compressor aerial drainage air of typical modern air-jet engine is up to the 20% of compressor gross exhaust gas.If flown Machine need not then specify the compressor aerial drainage for cabin pressurisation, and the part accounts for and always lets out in low-latitude flying or unmanned At least the 10% of stream.If turbine is not cooled, another of compressor air about 10% can be before it reaches burning It is extracted, this is using lower ignition temperature and therefore using cycle efficieny as cost.However, with novel metalloid material Progress and its high temperature and stress ability, the major part of turbine and certain high temperature section can be made of ceramic matric composite, no But the demand to cooling air is eliminated, but also is allowed for higher ignition temperature.Although for example, by non-cooled at present The turbine-entry temperature of metal parts limitation about 1750F is known as by those skilled in the art, but current CMC material It can support non-cooled 2000F turbines ignition temperature or higher.This causes considerably higher efficiency to recycle and most of In the case of mitigate engine weight, it is integrally advantageous to aircraft.If it is warm to be burnt using the 1750F of 20% compressor aerial drainage air Degree recycles non-cooled all-metal component engine by the 50% air drainage compressor that burns at 2000F by ceramic component Substitution, then cycle efficieny can be comparable, and the 50% of compressed air can be used for other purposes at compressor discharge station.

Table 1 shows this comparison, that is, the comparison be for have two of same units flow (that is, 1kg/s) it is non-cold But the various air drainages of engine and various aerial drainage percentages and the turbine that required input power is supplied to compressor Equal-wattage exports.The first row shows that the pressure ratio of cycle, the second row show compressor aerial drainage, shows that metal is sent out on the 3rd row Motivation Efficiency Calculation, and being shown compared with metal solution in last two rows, have under same efficiency similar aerial drainage and The thermal efficiency of the CMC schemes of maximum aerial drainage.General hypothesis is that turbine is uncolled in all cases, but in order to other Purpose, air come out from compressor aerial drainage.This is represented, if the aerial drainage percentage between metal solution and CMC schemes is kept Identical, then when circulating pressure ratio is more than 8, CMC engines become highly efficient.On the contrary, if the efficiency of engine is kept It is similar with the efficiency of metal solution, then it can significantly increase aerial drainage air percentage.This can also by explanation of such as getting off, That is, keeping the identical fuel flowing with burning, but air flowing is reduced, until (maximum metal is non-cold from 1750F for ignition temperature But technology) become 2000F (the non-cooled technologies of CMC) until.Compressor is balanced by generating identical power outlet from turbine Power entrance can make more compressor airs can be used for higher ignition temperature.Based on this, the present inventor has contemplated that A kind of cycle, that is, the cycle allows a large amount of compressor aerial drainage to be route via flow network and supply the enhancing of distribution The array of the array of thrust device, the enhancing thrust device is placed under the similar or preferable heat and whole efficiency of aircraft At the position of enhancing and improvement current techniques propulsive efficiency state.

Table 1

Therefore, conventional propeller cannot be scaled without significantly making its efficiency compromise.The reality of the present invention It applies example and current disadvantage is overcome by using improved cycle, the improved cycle eliminates the wind together with low-pressure turbine Fan system.As such, the embodiment of the present invention is a kind of system, the system is efficient, compact and highly integrated due to its Power-equipment and be particularly suitable for compared with flivver system and UAV, especially those be required to carry out VTOL and STOL operation be System.

Propeller with high-pressure turbine by placing " (chopped) of chopping " fan and high pressure compressed unit on the same axis At to form gas generator, be connected to injector and the conduit network of thrust augmentation injector.This is recycled by shredding The compressor assembly of fan (only core precommpression) and high pressure single-stage or compound compressor composition, the high pressure single-stage or multistage pressure Contracting machine is preferably the centrifugal compressor with several aerial drainage ports.Compressor aerial drainage port can be up to total in system with aerial drainage The 50% of air-flow, rest part is then directed into buner system.Burning is added under constant pressure or volume in the form of fuel Heating, and generate the thermal current for being directed toward turbine.Hot fluid is expanded into enter than the turbine in conventional expansion process by high-pressure turbine The low pressure and temperature of mouth pressure and temperature.Preferably, turbine and burning are to need high temperature that is less or not needing cooled flow Material, for example, modern times CMC.Turbine can be centripetal or axial, the turbine supply driving compression at least one grade Work needed for system.The exhaust of turbine is left under pressure and temperature more lower than the inlet condition of turbine, but is ring At least twice of the pressure of border air, and in the horizontal typical temperature of engine low for current turbine fan pressure turbine Under, that is, 1500F to 1800F.Thus, the expansion process of high-pressure turbine still results in high-energy, is not directed to low-pressure turbine High temperature and high pressure flowing is directed into the various positions for leading to the aircraft that propeller occurs for fluid thrust via conduit.

Conduit can also be insulation and utilization such as CMC high-temperature material.Receive pushing away for forced air or hot gas Carry and accelerate surrounding air in the first paragraph secretly using fluidics into device element；And by motive fluid and environment After air mixes and completes the thorough momentum transmission of from high-energy to low energy (surrounding air), make in the second diffuser Mixing flowing accelerate, to will be used as high pressure gas (being supplied to propeller from gas generator) and carry secretly surrounding air Mixture high-speed jet jet flow with high speed preferably and largely in axial direction convey, it is known in the art a certain Axial velocity profile.Each section of the entrainment rate of the thruster element in the high-pressure fluid of conveying is between 3 to 15 Between and up to 25.Due to being thoroughly mixed for higher entrainment and turbulent flow and flowing, the temperature of jet stream jet flow is correspondingly apparent It is lower.Follow the law that physics is transmitted about mixing and momentum, the speed of the jet stream jet flow from thruster element it is close but More than aircraft airspeed.Jet stream jet flow is substantially also non-circular, and the less rotative component that is with or without (is such as sent out with turbo-propeller The large-size propeller of motivation or even turbofan is opposite), and jet stream jet flow can be directed to aerofoil profile to generate Its portion of energy is further recycled after thrust, for example, towards before the short wing being placed at a certain distance from propeller rear Edge is guided to generate additional lift.In all embodiments, gas generator is the turbofan of modification, and wherein fan has been It is chopped into only to provide core flowing.

Figure 26 A show traditional bypass turbofan, by most of bypass of flowing and flow core It is mixed in the exit of turbofan with bypass flowing.Figure 26 B show the turbofan of the fan with chopping, only Core flowing and the aerial drainage from compressor is allowed to flow the thrust generated for needed for propulsion.As with gas generator 800 Hot arc 2602 is opposite, and the aerial drainage from compressor advantageously spreads all over cold section 2601 of gas generator 800 so that gas generator Allow maximal efficiency at 800 any time during operation.For example, when taking off, may require that more from compressor Aerial drainage, and the higher rate of rotor can be optionally advantageous.In the part of task, aerial drainage port be opened into so that Compressor operation is than no aerial drainage the case where far from surge line under more favorable state.Such as represented, the mesh in Figure 26 A Preceding turbofan can only be allowed for most 15% aerial drainages through task, but be cut by changing in an advantageous manner Broken fan design can induce more core flowings and more compressor aerial drainages, up to and include in the present invention Cross 50% aerial drainage of total air of engine.Just as skilled in the art will recognize, can also be related to more A aerial drainage makes aerial drainage at the relatively low stage maximize and makes aerial drainage at elevated pressures most to improve the efficiency of system Smallization.However, the amount for the flowing that especially application is only deliberately related in the cycle for aerial drainage in the present invention.From compressor The aerial drainage air of aerial drainage port is directed into the propeller of the thrust for enhancing via conduit, the propeller and aerofoil profile it is upper Pull together to place or be placed after aerofoil profile with higher incidence angle in surface.

Figure 27 A show the example of the aerial drainage and conduit network embodied in the present invention.The network includes gas generator 800, if feeding dry and cold thrust augmentation injector 801 and the spray of hot thrust augmentation via compressor aerial drainage port 251 and 351 respectively Emitter 901.As the signal from element 1702 (cold) and 1707 (heat) is fed to 900 (not shown) of microcontroller, pressure Flow measurement can be carried out with temperature sensor.It is sprayed from gas generator 800 to thrust augmentation via compressor aerial drainage conduit 251 The flowing of emitter 801 is indicated by control valve 1703, is controlled by microcontroller 900.Identical controller indicates rotary joint 1701 The actuating of (being used for element 801) and 1705 (being used for element 901).Figure 27 A further show a series of a cold thrust augmentation in four (4) Injector 801, they feed from the identical port 251 of the compressor of the gas generator 800 and are controlled by microcontroller 900 System.

Figure 27 B are shown such as similar network shown in Figure 27 A, but only there are two cold thrust augmentation injectors by pressing Contracting machine aerial drainage port is fed from gas generator 800.Rotary joint 1701 allows element 801 to rotate in a plurality of directions, and Fluid can also allow for pass to the injector 801.The injector relative to aircraft position from microcontroller 900 via electricity Dynamic or pneumatic or mechanical devices control.For measuring flow in the conduit in 251 downstream of aerial drainage port, pressure and temperature Sensor 1702 be used to information being fed to microcontroller.Then, microcontroller order element 801 surrounds rotary joint 1701 Rotation, while ordering to adjust via control valve 1703 and flow.Similarly, flow can be adjusted via control valve 1707 and about rotation Adapter 1705 adjusts the thrust size and orientation for being orientated and carrying out regulating element 901, until the position of aircraft is acceptable.Cause This, in addition to gas generator operating parameter and the thrust on each of thrust augmentation injector orientation and size with Outside, controller is also fed information from propulsion system conduit network.

Figure 27 C show microcontroller 900 and its network, show that a input at least 12 (12) and at least four (4) are a defeated Go out.The main control flow of output and thrust (injector) are orientated, so as to the posture for whenever controlling aircraft in its task.

Figure 27 D provide the details of more networks.Flowing from compressor aerial drainage port 251 and exhaust 351 is fed To thrust augmentation injector 801 and 901.The input for being input to microcontroller 900 via input 11 includes the ginseng of gas generator Number (rotating speed, compressor aerial drainage air themperature and pressure, pressure at expulsion and temperature, etc.).Input 26 includes coming to be included in be The feeding of accelerometer in system.Input 30 is gyroscope.Input 40 is ultrasonic wave or the air pressure for the height for signaling aircraft Height sensor inputs.Input 50 is GPS inputs.Input 70 is bluetooth input.Input 80 is R/C receivers.

In addition, Figure 27 D show the feedback from supravasal sensor to controller, such as fed information 2702 and 2706 institutes Show, flowing is adjusted for the actuating via control valve 1703 and 1707.Control valve is connected via cable 2703 and 2707 respectively To controller, and control valve is adjusted based on the input received from controller.By sensor 1702 and 1706 correspondingly adjustment and Flowing is measured, the sensor 1702 and 1706 provides feedback information to controller and is correspondingly adjusted to signal. Similarly, other sensors 11,26,30,40,50,60,70 and 80 are handled separately or together by controller, and via Cable 2701 and 2705 transmits the adjusting of the position of injector 801 and 901.

In another embodiment of the present invention, propeller can be rotated down to guide thrust to come for changing aircraft Posture, for taking off vertically or short takeoff.Figure 28 A to Figure 28 E show the possibility shape of the propeller in the present invention.Figure The system that 28A shows relatively simple quadrupole injector, the injector is by the gas generator feeding at center.The spray Two (cold) in emitter are fed with compressed air as power (or primary) air from compressor aerial drainage port, and thermal sprayer It receives and is vented from the exhaust port of gas generator.All four injectors refer to downwards, but via figure all in hovering pattern The variation for the parameter mentioned in 27A to Figure 27 D can adjust the posture of aircraft.Figure 28 B show the embodiment of the present invention, wherein One or more devices can be embedded in aircraft.In Figure 28 B, two cold injectors (two in four injectors are only shown A injector).Injector is flat, and is placed on the vertex rear of main wing, the mistake for expanding main wing Fast nargin is used with high speed jet is generated in the lift recurring structure of downstream.Flat injector can also be along wing Main shaft rotate for hovering (main downwardly directed ground) or for adjusting height in-flight.Figure 28 C are shown by four A injector (positioned at tail portion two thermal sprayers and be placed in two cold injectors at canard aerofoil profile rear) and embedded canard The more complicated canard system of injector composition in the housing system of (cold) injector side.Injector is flat and at it The main axial direction along flight generates the jet stream jet flow of rectangular shape at pelvic outlet plane.Alternatively, being shown with 3D in Figure 28 D The injector of element, wherein entrance and throat and diffuser are substantially 3D (rather than 2D), enhancing entrainment and globality Energy.The first half for only showing flat injector above wing in Figure 28 E is matched with the wing flap of the wing to be formed Complete structure only introduces secondary working fluid at the first half of injector (half injector is matched with the wing flap of wing).

Figure 29 shows a kind of possible cloth of the propulsion system in one embodiment of the invention when taking off or hovering It sets.To promote body and be maintained in hovering position under injector direction.

Figure 13 is shown provided with the navigability of the UAV of propulsion system.This is illustrated for tail portion (heat) and cold (canard) Pitching, rolling and the sideway positioning of both injectors.

In one embodiment of the invention, in this embodiment, compressor bleed air is received (in environmental air pressure Lower at least twice) and both hot gas jet flows (preferably at least twice environmental pressure) from high-pressure turbine propeller when taking off Under direction, therefore generation lifts off more than the propulsive thrust of UAV weight.United States Patent (USP) No.8,087,618 (Shmilovich et al.) discloses the use of such a device, and described device is embedded into aerofoil system and utilizes turbine Jet engine exhaust is for only guiding exhaust or compressed air and the small portion for utilizing compressor aerial drainage air when taking off Divide (being mentioned less than 15%) for controlling the additional flow of wing.In particular, in this way without increase thrust, and simply by Exhaust stream is controlled to make exhaust stream redirect with compressed air in take-off process.One embodiment of the present of invention is using specially The power-equipment of design, the power-equipment especially from compressor extraction be more than 20% aerial drainage air and flown to from Aerial drainage air is directed to the propeller in the entire flight course to land.Reaching the concrete mode of this purpose is：Pass through A kind of compressor is designed, there is the compressor the more open first order, the more open first order can accommodate more Flowing；Then the part largely flowed by aerial drainage, for example, up to total air flow 50%；And by the way that the part is drawn always Lead cold air propeller and by the way that the entire part of residue flowing is used for thermodynamic cycle, high-pressure turbine wherein after fluid Dump energy is directed into hot gas propeller.The flowing of compressor aerial drainage can also be modulated via using flow governor, example Such as, the control valve or fluid valve to propeller transport flow are modulated.The propeller of cold propeller and hot propeller both types Can be at least from 90 degree of rotations to 120 degree, and be independently directed toward under upper and direction compared with the direction of advance of flight.Cold air Body propeller can be embedded in or be hidden in wing or be preferably embedded in or be hidden in the first wing (duck of very high incidence angle The wing) wake flow in, and by the way that the entrance of propeller is placed near canard aerofoil profile and is preferably rested in its string most Enhance its stall margin in one third and closer to rear afterwards.Higher incidence angle can lead to separation and stall, but in institute The propeller of the rheme place of setting addition will make its operability much extend beyond stall point.

In another embodiment, the fluid of such as water or liquid nitrogen is injected with the cooling hot gas for being transported to hot propeller The takeoff thrust generated by the propeller can be increased by increasing the mass flow of Powered Air.If propulsion system quilt Be embedded into UAV, then the water on aircraft can make take off terminate with task after fuel on the aircraft almost disappeared The extra-push model of at least 25% and up to 50% will need not be added by landing when having consumed.

In yet another embodiment, the exhaust from high-pressure turbine is used as leading to primary/motive fluid of thermal sprayer Can be enhanced with additional cold air compressor aerial drainage, especially during horizontal flight, especially maintain to be fed into it is main pick into The colder temperature of the mixed feeding of the primary nozzle of device.In this way, mixing and reducing the temperature of admixture of gas under a constant In the case of, more long-life and/or less expensive material can be used in the catheter.The modulation of cold compressor air drainage can be with It is executed via valve, the valve, which will flow to be switched to from the cold propeller of supply, to be supplied the conduit of hot propeller or enter via secondary Mouth is switched to the pumping chamber of hot propeller to extend its service life.In this case, cold propeller becomes and host wing system pair It together or can be retracted in body, and therefore be not involved in thrust.

The thermodynamic cycle of typical jet engine is provided in Figure 30 A.The differentiation of working fluid is from the end of entrance (point 2) added under a constant via compression process to 3, via the isobaric procedure from 3 to 4 fuel and burning, from 4 to 5 It is expanded on turbine to describe.The latter provide by needed for compressor work(and additional energy, the additional energy can be used for driving It employs in the fan (via the turbine for being connected to fan) of turbofan or passes through for turbojet spray Mouth is expanded directly to air.The embodiment of the present invention eliminates the free turbine needed for driving fan, and the fan of chopping is connected The energy of burning gases at the main shaft of engine and point of use 45 with during the task of aircraft all the points (take off, Transition, horizontal flight, hovering and landing) at carried secretly via the injector of embedded aircraft specially designed and enhancing thrust.This hair The thermodynamics of bright cycle is developed 45 kinds of gases via almost constant entropy expansion more considerably higher than the expansion by turbine high Lower pressure is come under efficiency.Process 45-A' describes this differentiation, and may be considered that close to constant entropy, such as this type Nozzle expansion known there is very high efficiency.Working fluid develops 45-A' via multiple first in above-mentioned injector Grade slit occurs.In P_{2 is static}Under the conditions of, it is swollen to continue by constant pressure or constant region domains and the mixing of the surrounding air approached It is swollen.For working fluid, differentiation follows A' to D', and surrounding air is in from inlet condition point C to D' under constant pressure. During mixing under a constant, the final temperature of mixture enters the entrainment in injector depending on surrounding air Than.As described below, in the present invention using the injector specially designed, via several elements of the primary nozzle and injection The mixing section of device makes entrainment ratio maximize to more than 5：1 value (five parts of entrainment air are to every a primary working fluid).It connects down Come be pumping effect, the temperature and pressure of hotter secondary working fluid and the mixture of the surrounding air of entrainment is increased to respectively Temperature Τ_mixWith than P_EnvironmentHigh pressure P_{It is maximum}.This is the point D in the diagram of Figure 30 B.The approximate constant entropy of mixture is spread and spray It is to develop D to E to penetrate, and is respectively provided with final temperature T_OutletWith pressure P_Outlet, wherein P_OutletEqual to the environmental pressure under air speed. The positions point D are between point 2 and point 5, closer to point 2 to obtain higher entrainment ratio.Then, be the advantages of this system it is aobvious and It is clear to, it is noted that a large amount of air can be entrained and be encouraged to generate thrust under lower mixture temperature and speed. This makes the exhaust of this thermodynamic cycle be applied not only to thrust again, and in the exit of cycle, is additionally operable to advantageously The exhaust is directed on various aerofoil profiles and is occurred for additional lift, or makes the exhaust vector for aircraft VTOL and STOL abilities.In addition, in certain embodiments, the placement of the entrainment entrance of the injector can make from such as Boundary layer sucking caused by the aerofoil profile of wing causes the additional benefit for assisting the stall margin of aerofoil profile wing.In one embodiment In, first group of air-foil, which is so positioned into, makes it be operated with very high incidence angle, and has very small stall Nargin.After the injector is just placed on the aerofoil profile vertex, in the region for being easy to develop boundary layer separation, Suction side (that is, the entrainment side of injector or entrance side) determines that stall margin is enhanced considerably, to allow in the aerofoil profile/machine Very high lift is generated on the wing to obtain stall freedom.

In addition, desired short takeoff distance in some cases, the exhaust from turbofan can be drawn In the suction side for leading aerofoil profile (for example, wing flap).Although this technology has used several concepts, limits and finished Fruit.In this embodiment of the invention, at least for being exposed to the part for the wing that thrust component gushes out jet stream, there are The relatively high-lift proportional to higher local velocity square, this is because it utilizes following benefit, that is, will be compared with kinetic energy fluid (air of the mixture of exhaust) be conducted directly to wing or wing flap on the pressure side rather than suction side or with turbomachinery aerofoil profile (example Such as, turbine) mode be directly largely directed to leading edge.

In addition, the exhaust of injector is at significantly lower temperature and has the average outlet speed higher than air speed again The exhaust of degree, the injector can be guided towards secondary downstream thin airfoil.Injector by its jet towards thin and It can be guided by the aerofoil profile for the composite material manufacture reinforced.Compared with the lift generated by the aerofoil profile, higher jet speed Degree determines that the relatively high-lift in the aerofoil profile, the aerofoil profile then only receive the air speed flowing of aircraft.On the contrary, the size of aerofoil profile It can be significantly reduced with shape to generate the lift similar with very big wing.Turning now to the entrance and note of injector Anticipating, they are just placed on the top of aerofoil profile 803, and the vertex that the aerofoil profile 803 is crossed in the sucking in boundary layer is developed in injector, And the better stall margin of aerofoil profile 803 is determined by the boundary layer that the injector sucks and allow aerofoil profile 803 with compared with High incidence angle efficiently operates.

In another embodiment shown in Figure 31, the cold injector 801 is placed on rear and the wing of aerofoil profile 803 The front of type 802, it is abundant still through the stall increased caused by the suction in the boundary layer of the aerofoil profile 803 in aerofoil profile 803 Lift carrys out shadow caused by the fair speed of degree and the jet due to efficiently being guided towards aerofoil profile 802 in 801 ' exit Ring both aerofoil profile 803 and aerofoil profile 802.This allows both aerofoil profile 803 and 802 to be located at more positive horizontal flight position, compared with short limb Same lift of the type for injector takes off vertically, hovers with rotation and the manipulation of aircraft.Also allow more advantageously to make It is used, rather than wasted into environment with being directed to lift with the jet of thermal device, as the prior art The case where current state of jet engine.

Although this is not meant to be detailed list, different embodiments of the invention are designed to provide following change Into with some or all in advantage：

Enhance following ability, that is, the ability is to make under all flying conditions from coanda formula flat jet The thrust augmentation and vector quantization of jet stream jet flow maximize；

Efficiency is improved via specific 3D features are introduced in primary nozzle and Coanda surface and shortening is used for and aircraft Wing or the preferably integrated device of fuselage；

This device insertion wing is improved to the efficiency of aircraft with the geometry in particular using wing；

Primary nozzle efficiency is improved via additional feature to carry secondary fluid and the shortest time section in device and length secretly Mixing in degree；

Enhance overall geometry in a manner of non-circular to allow it in the aircraft in addition to taking off, hovering and landing Efficient operation in horizontal flight, while improving the propulsive efficiency of aircraft and eliminating on the wing and fuselage of engine nacelle and aircraft Main engine presence；

By using the remaining kinetic energy for the jet stream jet flow for usually only generating thrust via mechanical connection, since jet flow is in wing On higher local velocity, generate additional thrust and lift；

The diffuser wall with the propeller of lifting system is being promoted to keep the same of identical lift by extending to be used as When, shorten wing；

Injector is improved with (the example that preferably works under conditions of the ideal conditions of the injector far from fixed geometirc structure Such as, operation is optimized by using the two half-unit of injector and promotes thermodynamic cycle, them can be made to transport relative to each other It moves and adds wing flap shape feature so that the expansion and contraction completely of injector diffuser wall)；

Due to the lower temperature of jet stream jet flow mixture occurred from propeller and in the fast axial speed than aircraft Spend component, increase each span than lift；

Since it can bear the higher temperature of the mixture jet stream jet flow occurred, it is used in so being used as including composite material The type of material in thin airfoil；

Because aerofoil profile can be with thinner width and the shorter span and with higher mechanical resistance stress performance, institute To reduce the overall dimension and weight of aircraft；

Via the flowing for both rotating and adjusting propeller and aerofoil profile, it is significantly improved the navigability of aircraft and multi-functional Property, including it is allowed for V/STOL and hovering；And/or

By the compact systems for being allowed for that there is small swing and distributed propulsion system, especially in UAV, UAS and nothing In man-machine, enhance the ability of aspect control, hovering and VTOL.

In addition, other than many features above-mentioned, different embodiments of the invention can also have following improvement With some or all in advantage：

Thermodynamic cycle is simpler, and wherein injector/injection type element replaces entire fan and low-pressure turbine subsystem Functionality, therefore the weight of system is reduced at least 30%.This due to being explained above for causing turbofan to be imitated It is especially advantageous for the not high smaller UAV types system of rate；

Injection type propeller can be independently rotated in the case where not moving larger rotatable parts or make its arrow Quantify and is allowed for vertically take-off and landing；

It can be in the stream for taking off with flowing to these propellers during horizontal flight and in landing with modulation when emergency It is dynamic, therefore apply different thrust levels at each position of aircraft and be kept completely separate any amount of propulsion Device；

The non-moving parts of same functionality can be used to eliminate larger rotatable parts, that is, use liquid propeller/injector generation For fan；From non-moving parts to rotatable parts, it is contemplated that component life directly improves, and the size requirement particularly with fan is non- For the small UAV and aircraft of normal high speed；

For conduit and propeller, the lightweight and height of such as composite material, carbon fiber-based material and CMC can be used Adiabator；

Aerial drainage can be modulated so that only supply hot gas to hot propeller in horizontal flight or supply comes from gas generator Thermal exhaust and colder compressor air aerial drainage mixture；

Following benefit, that is, gas generator operates under optionally advantageously identical rotating speed, between taking off and cruising RPM larger offset without far from surge line or stall line；

Following benefit, that is, assign propeller any shape and can significantly be integrated with the fuselage and wing of aircraft；

Following benefit, that is, there is larger entrainment and turbulent closure scheme in the propeller so that from their exhaust Jet stream jet flow temperature be low enough to allow aerofoil profile for aircraft lift or gesture stability and exist and suitably play work( Can, including the jet stream of fair speed is used to generate more lift；And/or

Following benefit, that is, by propeller in the flare angular vertex rear of wing insertion wing, in the flare of the wing At angular vertex boundary layer will in other ways with higher incidence angle detach, be consequently inhaled the boundary layer and delay its detach and Increase stall margin of the wing in horizontal flight.

It should be noted that can using any injector geometry described herein come configure injector 701,801, Any of 901.

Although aforementioned texts elaborate the detailed description of many different embodiments, will it should be understood that protection domain by The word of the claims followed limits.Detailed description is only interpreted as illustratively, and without describing each may Embodiment, even if this is because it is also unpractical that each possible embodiment of description, which is not impossible,.It can use Current techniques or the technology developed after present patent application day realize that many alternative embodiments, these embodiments will still So fall within the scope of the claims.

Therefore, skill that can be in the case where not departing from the spirit and scope of the claims to being described herein and showing Art and structure carry out many modifications and variations.Therefore, it should be understood that method described herein and equipment are merely illustrative, and And do not limit the range of claims.

Claims (23)

1. a kind of aircraft comprising：

Main body, the main body have preceding part, portion, starboard side and port side；

Gas generator, the gas generator are connected to the main body and generate gas stream；

At least one front conduit, at least one front conduit are fluidly coupled to the generator；

At least one tail portion conduit is connected to the generator at least one tail portion catheter fluid；

First front injector and the second front injector, first front injector and the second front injector fluid Ground is connected at least one front conduit, is connected to the preceding part and is respectively coupled to the starboard side and larboard Side, the front injector respectively include export structure, and the gas from least one front conduit is tied from the outlet Structure is flowed out with the predetermined speed that can be adjusted；

At least one tail portion injector, at least one tail portion injector are fluidly coupled at least one tail portion conduit And it is connected to the portion, at least one tail portion injector includes export structure, comes from least one tail portion The predetermined speed outflow that the gas of conduit can be adjusted from the export structure；

With the up-front first primary foil element and the second primary foil element, the primary foil element is respectively coupled to institute State starboard side and port side, the leading edge of the described first primary foil element and the second primary foil element is respectively located immediately at described The downstream of first front injector and second front injector so that the gas from the front injector flows through described The leading edge of primary foil element；And

At least one secondary foil element, at least one secondary foil element have leading edge and are connected to the main body, The downstream of export structure of the leading edge of at least one secondary foil element located immediately at least one tail portion injector, So that the gas from least one tail portion injector flows through the leading edge of at least one secondary aerofoil profile.

2. aircraft according to claim 1 further includes the first canard and the second canard, first canard and described Two canards are connected to the preceding part and are respectively coupled to the starboard side and port side, and the canard is configured as when described The boundary layer of the surrounding air of the canard is flowed through in development when aircraft is in movement, and the canard is respectively located immediately at described The upstream of first front injector and second front injector so that first front injector and second front Injector is fluidly coupled to the boundary layer.

3. aircraft according to claim 2, wherein first front injector and second front injector point Not Bao Kuo first entrance part and second entrance part, and first front injector and the second front injector quilt It is located so that the boundary layer is sucked by the intake section.

4. aircraft according to claim 1, wherein the gas generator is disposed in the main body.

5. aircraft according to claim 1, wherein the gas stream generated by the generator is to promote the aircraft The only resource.

6. aircraft according to claim 1, wherein first front injector and second front injector are each From with leading edge, and in each of first front injector and second front injector it is whole can surround with The parallel-oriented axis rotation of the leading edge.

7. aircraft according to claim 1, wherein first front injector and second front injector are each From with leading edge, and in each of first front injector and second front injector it is whole can surround with The axis rotation that the leading vertical is orientated.

8. aircraft according to claim 1, wherein at least one tail portion injector has leading edge, and described The entirety of at least one tail portion injector can be surrounded to be rotated with the parallel-oriented axis of the leading edge.

9. aircraft according to claim 1, wherein at least one tail portion injector has leading edge, and described The entirety of at least one tail portion injector can surround the axis being orientated with the leading vertical and rotate.

10. aircraft according to claim 1, wherein at least one of described export structure is non-circular.

11. aircraft according to claim 1 further includes cabin portion, the cabin portion is configured as realizing Someone of the aircraft operates.

12. aircraft according to claim 1, wherein：

The gas generator include the wherein described gas stream be in low temperature first area and the wherein described gas stream be in height The second area of temperature；

At least one front conduit provides the gas from the first area to first front injector and institute State the second front injector；And

At least one tail portion conduit provides the gas from the second area at least one tail portion injector.

13. a kind of aircraft comprising：

Main body, the main body have preceding part, portion, starboard side and port side；

Gas generator, the gas generator are connected to the main body and generate gas stream, and the gas generator includes The wherein described gas stream is in the first area of low temperature and the wherein described gas stream is in the second area of high temperature；

At least one front conduit, at least one front conduit are fluidly coupled to the generator；

At least one tail portion conduit is connected to the generator at least one tail portion catheter fluid；

First front injector and the second front injector, first front injector and the second front injector fluid Ground is connected at least one front conduit, is connected to the preceding part and is respectively coupled to the starboard side and larboard Side, the front injector respectively include export structure, and the gas from least one front conduit is tied from the outlet Structure is flowed out with the predetermined speed that can be adjusted, and at least one front conduit provides the gas from the first area to institute State the first front injector and second front injector；And

At least one tail portion injector, at least one tail portion injector are fluidly coupled at least one tail portion conduit And it is connected to the portion, at least one tail portion injector includes export structure, comes from least one tail portion The predetermined speed outflow that the gas of conduit can be adjusted from the export structure, at least one tail portion conduit will come from described The gas of second area is provided at least one tail portion injector.

14. aircraft according to claim 13 further includes having the up-front first primary foil element and the second primary Foil element, the primary foil element are respectively coupled to the starboard side and port side, the described first primary foil element and The leading edge of second primary foil element is respectively under first front injector and second front injector Trip so that the gas from the front injector flows through the leading edge of the primary foil element.

Further include the first canard and the second canard 15. aircraft according to claim 13, first canard and described Second canard is connected to the preceding part and is respectively coupled to the starboard side and port side, and the canard is configured as working as institute The boundary layer that the surrounding air of the canard is flowed through in development when aircraft is in movement is stated, the canard is respectively located immediately at institute State the upstream of the first front injector and second front injector so that before first front injector and described second Portion's injector is fluidly coupled to the boundary layer.

16. aircraft according to claim 15, wherein first front injector and second front injector Respectively include first entrance part and second entrance part, and first front injector and second front injector It is positioned such that the boundary layer is sucked by the intake section.

17. aircraft according to claim 13, wherein the gas generator is disposed in the main body.

18. aircraft according to claim 13, wherein first front injector and second front injector Respectively there is leading edge, and entirety in each of first front injector and second front injector can surround It is rotated with the parallel-oriented axis of the leading edge.

19. aircraft according to claim 13, wherein first front injector and second front injector Respectively there is leading edge, and entirety in each of first front injector and second front injector can surround It is rotated with the axis that the leading vertical is orientated.

20. aircraft according to claim 13, wherein at least one tail portion injector has leading edge, and institute The axis rotation parallel-oriented with the leading edge can be surrounded by stating the entirety of at least one tail portion injector.

21. aircraft according to claim 13, wherein at least one tail portion injector has leading edge, and institute The axis rotation being orientated with the leading vertical can be surrounded by stating the entirety of at least one tail portion injector.

22. aircraft according to claim 13, wherein at least one of described export structure is non-circular.

23. aircraft according to claim 13 further includes cabin portion, the cabin portion is configured as realizing Someone of the aircraft operates.